PROGRESS REPORT NO. 9 DIESEL ENGINE IGNITION AND COMBUSTION Effect of Type of Fuel, on Ignition Delay Engine Speed, and. Coolant Temperature and. Other Combustion Phenomena JAY A. \\BOLT N. A. HENEIN PERIOD JANUARY 1, 1968 TO JUNE 30, 1968 OCTOBER 1968 U. S. Army Tank-Automotive Center Warren, Michigan and. is work performed. by the: Department of Mechanical Engineering The University of Michigan Ann Arbor, Michigan under Contract No. DA-20-018-AMC-1669(T)

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DISTRIBUTION LIST Contract Distribution Name and Address U. S. Army Tank-Automotive Center Propulsion Systems Laboratory Warren, Michigan 48090 Attention: SMOTA-RCP Internal Distribution Professor J. A. Bolt Professor E. T. Vincent Professor N. A. Henein No. of Copies I 1. 2 iii *~ * 1S1

TABLE OF CONTENTS Page LIST OF TABLES vi LIST OF FIGURES vii Part I: Summary I. BACKGROUND 3 II. OBJECTIVES 4 III. CUMULATIVE PROGRESS A. Lister-Blackstone Engine B. ATAC-1 Open Combustion Chamber Engine 1. Engine instrumentation 2. Experimental work on ATAC 3. Theoretical analysis 6 IV. PROGRESS DURING THIS PERIOD '7 V. CONCLUSIONS 8 A. Effect of Type of Fuel on I.D. and Heat Release Rate 8 B. Effect of Speed on Ignition Delay, Smoke, Wall Temperataure, and. Thermal Loading 9 1. Effect of engine speed on ignition delay 9 2. Effect of speed on smoky intensity 9 3. Effect of speed. on wall temperatures 9 4. Effect of speed on thermal loading 9 C. Effect of Coolant Temperature on Combustion Phenomena 10 1. Effect of coolant temperature on ignition delay 10 2. Effect of coolant temperature on thermal loading 10 3. Effect of coolant temperature on after injection 10 VI. PROBLEM AREAS AND CORRECTIVE ACTIONS 11 A. Fuel Leakage Past Pump-Plunger 11 B. Failure of Pressure Transducer 11 C. Surface Thermocouple Failures 11 D. Engine Vibration 11 VII. FUTURE PLANS 12 iv

TABLE OF CONTENTS Page A. Next Period 12 B. Overall 12 VIII. SIGNIFICANT ACCOMPLISHMENTS 13 Part II: Instrumentation, Experimental, and Analytical Results I. INSTRUMENTATION 17 A. Fire Deck Wall Temperature 17 B. Coolant Flow Rate 17 C. Temperature Rise of Coolant Across the Engine 1.7 D. Lubricating Oil Flow Rate 17 E. Temperature Drop Across the Oil Cooler 17 II. HEAT RELEASE COMPUTATIONS AND RESULTS 23 III. EFFECT OF SPEED ON IGNITION DELAY AND-OTHER COMBUSTION PHENOMENA 52 Al. Effect of Speed on I.D.p at Mean Pressure = 500 psia 32 A2. Effect of Speed on I.D.p, Mean Pressure - 700 psia 33 B. Effect of Speed. on Smoke Intensity 39 C. Effect of Speed on Combustion Chamber Wall Temperatures 39 D. Effect of Speed. on Thermal Loading 42 IV. EFFECT OF COOLANT TEMPERATURE ON IGNITION DELAY AND OTHER COMBUSTION PHENOMENA 44 A. Effect of Coolant Temperature on Combustion Phenomena 45 B. Effect of Coolant Temperature on Thermal Load 45 C. Effect of Coolant Temperature on Injection Process 45 V. PISTON AND LINER INSPECTION AFTER THE HIGH COOLANT TEMPERATURE TESTS 50 APPENDIX A: COMPUTER PROGRAMS 51 APPENDIX B: TABLES 119 APPENDIX C: REFERENCES 125 V

LIST OF TABLES Table Page 1. Effect of Engine Speed on Ignition Delay Using CITE Fuel at a Mean Pressure of 500 psia During the Ignition Delay 120 2. Effect of Engine Speed on Ignition Delay Using CITE Fuel at a Mean Pressure of 700 psia During the Ignition Delay 121 3. Effect of Coolant Temperature on Ignition Delay 122 4. Equivalent Area for Fuel Flow in Injector Nozzle Versus Needle Lift 123 vi

LIST OF FIGURES Figure Page 1. Position of thermocouples in the fire deck near the intake and exhaust valve seats. 18 2. Closed, cooling system for the use of ethylene-glycol at high temperatures. 19 35 Photograph of the closed. cooling system for ATAC-1 engine. 20 4. Photograph of the coolant flow meter. 21 5. Lubricating oil cooling system. 22 6. Pressure trace for ATAC-1 engine plotted by the computer. 25 7. Fuel pressure and needle lift traces for ATAC-1 engine plotted, by the computer. 26 8. Rate and accumulated fuel injection for ATAC-1 engine plotted by the computer. 27 9o Detailed pressure trace for ATAC-1 engine during combustion. 28 10. Heat release diagram for ATAC engine with CITE Fuel plotted. by the computer. 29 11. Heat release diagram for ATAC engine with diesel no. 2 fuel plotted by the computer. 31 L2. Effect of engine speed on ignition delay at a mean pressure of 500 psia. 34 L35 Corrected ignition delay versus engine speed (reference temperature = 161990R). 35 14. Effect of engine speed on ignition delay at a mean pressure of 700 psia. 37 15. Effect of speed on the mean gas temperature during the ignition delay. 38 16o Effect of speed on smoke intensity. 40 vii

LIST OF FIGURES (Concluded.) Figure Page 17. Effect of engine speed. on wall temperature. 41 18. Effect of engine speed. on thermal loading. 43 19. Effect of coolant temperature on thermal loading. 46 20. Effect of coolant temperature on % heat lost to coolant and. lubricating oil. 47 21. Effect of coolant temperature on needle lift during after injection. 48 22. Needle lift diagrams with coolant temperatures of 217~F and 304.3~F. 49 23. Equivalent area for fuel flow in injector nozzle versus needle lift. 124 viii

PART I SUMMART 1

I. BACKGROUND A program of activity to study the combustion process in supercharged. diesel engines has been developed at The University of Michigan. This program is primarily concerned with the ignition delay and the effect of the several parameters on it. A special concern is given to the effect of the pressure and temperature of the cylinder air charge and engine speed on ignition delay. The program also includes the study of the effect of these variables on the other combustion phenomena such as smoke, rate of pressure rise, and. maximum pressure reached in the cylinder. The different types of delay have been studied in detail and an emphasis is made on the pressure rise delay and. illumination delay. The instruments needed for the measurement of these two delay periods have been developed and a continuous effort is being made to improve their accuracy. This research is being made on two experimental diesel engines. One is the ATAC high output open combustion chamber engine, and the other is a ListerBlackstone swirl combustion chamber engine. Three fuels have been used in these tests. 3

II. OBJECTIVES A. To study how gas pressure at the time of injection affects ignition delay and. combustion. The effects are to be studied at pressures ranging from approximately 300 to 1000 psiao BO To study how gas temperature at the time of injection affects ignition delay. The temperature ranges from approximately 900~F to 1500~F. C. To study various combinations of pressures and. temperatures to determine whether density is an independent variable affecting ignition delay. D. To conduct all these studies with three funels: CITE refree grade (MilF-45121) fuel, diesel no. 2 fuel, and. Mil-G-3056 refree grade gasoline. E. To study the effect of engine speed. on the ignition delay and. the other combustion phenomena. The engine speed. covered a range from 1000 rpm to 3000 rpm. F. To study the effect of the coolant temperature on the combustion process and the wall temperatures. Coolant temperatures range from 150~F to 300~F. G. To study the effect of anti-smoke additives on the combustion process and the smoke. The anti-smoke additive is Lubrizol barium compound. 4

III. CUMULATIVE PROGRESS A. LISTER-BLACKSTONE ENGINE Cumulative progress has been made in the following areas: A. Review and analysis of previous work B. Theoretical analysis C. Experimental work on Lister-Blackstone engine D. Comparison between the present work d.one on the Lister engine and. previous work in bombs and. engines B. ATAC-1 OPEN COMBUSTION CHAMBER ENGINE The cumulative progress made on ATAC-1 engine can be devided into three major areas: 1. Engine instrumentation 2. Experimental work 3. Theoretical work 1. Engine Instrumentation The engine has been instrumented and all the instruments calibrated, to measure the following: a. Power output and engine speed b. Gas pressure during the cycle c. Illumination due to combustion d. Wall surface temperature during the cycle e. Wall temperature in the fire deck near the inlet and. exhaust valves f. Fuel pressure before the injector g. Injector needle lift h. Air flow rate into the engine and its temperature and pressure before the inlet valve i. Fuel. flow rate j. Intensity of smoke in the exhaust gases, their temperature and pressure;. Experimental Work on ATAC Experiments were made on the ATAC engine to study the effect of temperature 5

on ignition delay and combustion characteristics of the following fuels: a. CITE refree grade (Mil-F-45121) fuel b. Diesel no. 2 fuel c. Mil-G-3056 refree grade gasoline fuel The experimental results of this part were given in Progress Report No. 8, under A2A, A2B, A2C, and. A2D series~ 3. Theoretical Analysis A thermodynamic analysis was made to study the different types of energy and processes taking place during the ignition delay, and to compare between the different definitions used in the literature for the ignition delay. This study will be published. in an SAE paper which will be presented. in the International Meeting in Detroit, on January 17, 1969. 6

IV. PROGRESS DURING THIS PERIOD During this period the experimental and analytical work on the ATAC engine has been completed., as follows: a. A comparison between the combustion phenomena and the rate of heat release for the following fuels, under natiral1y aspirated conditions. The series of tests conducted for this comparison is referred to as series AI. 1. CITE refree grade (Mil-F-45121) fuel 2. Diesel no. 2 fuel, and 3. Mil-G-3056 refree grade gasoline fuel The experimental work demonstrated that it was difficult to burn gasoline in the ATAC engine with its present compression ratio of 16.7:1, under naturally aspirated conditions. The heat release computations were therefore only made for CITE and. diesel no. 2 fuels. The several computer programs made —for these elaborate computations proved. to be very successful, and. can be- used in future heat release computations under any set of running conditions. b. Effect of engine speed on the ignition delay and other combustion phenomena. Engine speeds covered a range from 1000 rpm to 3000 rpm. c. Effect of coolant temperature on the combustion process of CITE fuel. The coolant used for these tests was ethylene glycol at temperatures up to 305F. 7

V. CONCLUSIONS The conclusions are stated under the following headings: A. Effect of type of fuel on I oD. and heat release rate B. Effect of engine speed, on I.D. and other combustion phenomena C. Effect of coolant temperature on the different combustion phenomena A. EFFECT OF TYPE OF FUEL ON I.D. AND HEAT RELEASE RATE The results of the heat release computations, for the diesel no. 2 and. CITE fuels, showed, that the following processes occur during the ignition delay before the pressure rise due to combustion is detected: 1. A negative heat release at the beginning of the ignition delay, due to fuel evaporation and. the endothermic reactions that take place shortly after fuel injection. The negative heat release is observed for the two fuels during a major part of the ignition delay. 2. The negative heat release is followed by very slow reactions causing a slight increase in the rate of heat release. The end of the pressure rise delay measured from the pressure trace, coincides with the end of these slow reactions, before the start of the very high speed reactions. The negative heat release period as well as the total ignition delay period are shorter for diesel no. 2 fuel than for CITE fuel. These results support the previous conclusions reached., 1 thati the activation energy for diesel no. 2 fuel is smaller than that for CITE fuel, causing the preignition reactions for the diesel fuel jto be faster and. the delay period shorter than for the CITE fuel. The ignition delay is followed. by a period of very rapid or explosive type reactisons during which the energy of reaction of the fuel is released. These:reactions occupied a relatively short period. compared with the total ignition delay. The maximum rate of heat release for the diesel fuel was found. to be about 75% of that for CITE fuel. *Numbers refer to list of references. 8

B. EFFECT OF SPEED ON IGNITION DELAY, SMOKE, WALL TEMPERATURE, AND THERMAL LOADING 1. Effect of Engine Speed on Ignition Delay The apparent effect of the increase in engine speed. is to decrease the ignition delay. However, if a correction is made for the effect of increase in the charge temperature with speed., the ignition delay was found, to increase with speed.. The conditions of the tests carried out to study the effect of speed on ignition delay were carefully adjusted to eliminate the change in any parameter other than the engine speed. 2. Effect of Speed on Smoky Intensity An increase in speed. from 1500 rpm and 3000 rpm caused an increase in the smoke intensity from 40 to 60 Hartridge units. 3. Effect of Speed on Wall Temperatures The increase in speed produced the following effects in the wall temperature at the different locations in the cylinder head. a. The wall surface temperature in the valve bridge of the fire deck increased at a high rate with the increase in speed from 1000 rpm to 2000 rpm, after which the temperature leveled off. At 1000 rpm the surface temperature was 435~F and reached 509~F at 2900 rpm. b. The swing in the surface temperature decreased from 370F at 1000 rpm to 13~F at 2900 rpm. c. The wall temperature at the midpoint between the gas side and coolant side in the fire deck showed a different trend.. (1). near the exhaust valve the temperature increased from 326~F at 1000 rpm to 360~F at 2900 rpm. (2). near the inlet valve the temperature remained constant at about 267 F. 4. Effect of Speed on Thermal Loading The thermal loading which is equal to the sum of the heat lost to the water jackets and lubricating oil increased, with speed. However, the thermal loading as a percentage of the heat input in the fuel decreased from 20% at 9

1000 rpm to 14% at 2900 rpm. C. EFFECT OF COOLANT TEMPERATURE ON COMBUSTION PHENOMENA 1. Effect of Coolant Temperature on Ignition Delay The increase in the ignition delay. mean pressure of 700 the coolant temperature from 156~F to 305~F did. not affect The value of I.D.p over the whole temperature range at a psia was 0.680 millisecond. 2. Effect of Coolant Temperature on Thermal Loading The increase in coolant temperature reduced the percentage heat loss to the coolant and. lubricating oil from 17.7% at 156~F to 13.8% at 3050F. The total heat loss decreased. from 1660 Btu/hp. hr. at 156~F to 1230 Btu/hp. hr. at 305~F. 3. Effect of Coolant Temperature on After injection The increase in coolant temperature caused. the after injection to d.ecrease till a temperature of about 230'F, after which it increased, again. 10

VI. PROBLEM AREAS AND CORRECTIVE ACTIONS A. FUEL LEAKAGE PAST PUMP-PLUNGER Problem: Excessive leakage of CITE fuel past the pump plunger and dilution of the lubricating oil in the sump. Corrective Action: A new pump was installed. B. FAILURE OF PRESSURE TRANSDUCER Problem: Failure of fuel line pressure transducer type 601H. Corrective Action: To avoid any delay in the progress of the experimental work a dummy transducer was made and. installed. C. SURFACE THERMOCOUPLE FAILURES Problem: Failure of surface thermocouple. Corrective Action: Design and manufacture of a new adaptor to relieve the tightening stress in the thermocouple body. The assembled body of a new thermocouple and adaptor were installe d in the cylinder head. with the thermocouple surface flush with the inside wall surface. D. ENGINE VIBRATI ON Problem: Excessive vibration of the engine was noted at high speeds (above 2800 rpm). Corrective Action: The balancing weights were checked and the left balancing shaft found. 900 ahead of the position indicated. in the drawings. The front plate of the auxiliary drive was taken off and. the shaft position adjusted. to conform with the engine specifications. 11

VII. FUTURE PLANS A. NEXT PERIOD 1. Experimental. Run tests on ATAC open chamber engine to find the effect of anti-smoke additives on the ignition delay and the rate of heat release. 2. Publication of part of the results in national meetings. To prepare a paper to be presented to the SAE on "Correlation of the Air Charge Temperature and. Ignition Delay for Several Fuels in a Diesel Engine." Permission for this publication has been requested from ATAC. B. OVERALL 1. Experimental. To complete the runs on the effect of gas pressure on the ignition delay and. other combustion phenomena. 2. Analytical. To study the effect of pressure on the ignition delay, and to compare the results obtained on the ATAC engine and the results of previous work done in bombs and engines. 12

VIII SIGNIFICANT ACCOMPLISHMENTS The paper presented. before the Society of Automotive Engineers in January, 1967, covering the experimental results on the Lister-Blackstone engine will be published in the SAE Transactions of 1968. The title of this paper is "Ignition Delay in Diesel Engines," by the authors of this report. The computer programs made for the calculation of the rates of heat release proved to be successful. The results reached reflect the accuracy with which the experimental and. analytical data have been taken. These computer programs are now ready to study the effect of fuel additives on the combustion process and rates of heat release. 13

PART II INSTRUMENTATION, EXPERIMENTAL, AND ANALYTICAL RESULTS Ad.ditional instrumentation made during this reporting period has included means to measure the wall temperatures, thermal loads on the cooling and. lubricating systems, including the high coolant temperature running conditions. The experimental and analytical results covered. the following areas: A. Heat release computations and results. B. Effect of speed on ignition delay and. other combustion phenomena. C. Effect of coolant temperature on ignition delay and other combustion phenomena. 15

I. INSTRUMENTATION During this period, the engine was instrumented to measure the following: A FIRE DECK WALL TEMPERATURE The temperature of the metal midway between the gas and. coolant sides of the fire deck was measured. by an iron-constantan thermocouple. Two thermocouples were used, to measure the temperature at a radial distance of 1/8 in. from the exhaust the inlet valve inserts. The position of these thermocouples is shown in Fig. 1. B. COOLANT FLOW RATE The cooling system piping was changed to allow the use of a closed. system with a heat exchanger, as shown in Figs. 2 and 3. The coolant flow rate was measured by a standard ASME sharp edge orifice as shown in Fig. 4. The coolant used was ethylene-glycol. C. TEMPERATURE RISE OF COOLANT ACROSS THE ENGINE The rise in the coolant temperature from its entrance to the exit from the engine was measured by two iron-constantan thermocouples. This temperature rise and. the coolant flow rate were used. to calculate the thermal load. on the cooling system. D. LUBRICATING OIL FLOW RATE The rate of flow of the lubricating oil was measured by a turbine type meter. The oil was cooled in a heat exchanger to a constant temperature of 2000F. The oil cooling system is shown diagramatically in Fig. 5. E. TEMPERATURE DROP ACROSS THE OIL COOLER The increase in oil temperature across the engine was measured by two ironconstantan thermocouples. This was used to calculate the thermal load on the lubricating system. 17

OH ID~~~~~~~~~~~~~~~~~~~~~~~I I - I 8 Drill 48 1.930 '1 1/8" 1/8' — IN 1.750' Fig. 1. Position of thermocouples in the fire deck near the intake and exhaust valve seats.

Sight Gloss Tout ATAC-1 Engine H \-J kO Water inlet to coolant heat exchanger fl '-_:T'I -— st Thermostat L o__zi Water out to drai Main air ~ supply Valve Air line to (manually operated) thermostat Air supply to Diaphragm Valve' diaphragm valve Fig. 2. Closed cooling system for the use of ethylene-glycol at high temperatures.

Fig. 3. Photograph of the closed cooling system for ATAC-1 engine. 20

Fig. 4. Photograph of the coolant flow meter. 21

'AAl~J"l '~ Oil Filter ump Tout- 'Oil Flowmeter Tout (Turbometer) =~ ---___ |Cooling Water Exchanger Fig. 5. Lubricating oil cooling system. Heat 22

II. HEAT RELEASE COMPUTATIONS AND RESULTS The rate of heat release in the ATAC engine, during the combustion process was calculafted for diesel no. 2, and CITE fuels, under the following running condi-tions: Fcel Diesel No. 2 CITE (Mil.F-451.21) Pressure in surge tanks, in. Hg ab solut e inlet. air tempera'ture, OF Pcel-air ratio Injector opening pressure, psia (static) injector timing, (dynamic) degrees before T.DoC. Engine speed., rpm Coolantl temperature at outlet, ~F 29.3 96.0 o. 0o301 3000.0 2002 2001 0 174.0 29. 4 940 o. 0299 3000. O 20o3 2000~ 0 170.0 The following traces were observed. on graphed by the polaroid camera. the oscilloscope screen and photo~ ao Gas pressure-crank angles b PFuel presscure ---crank angles c. Needle lifti,-crank angles C4 SSurface wall temperatuLre-crank angles The gas pressurecerank angles trace was taken for the whole cycle arld.:for s c-cessive divisions of the cycleo The duration of each divi.sion depend, on 'tjhe events taking place in the cycle during this division~ In some cases a photograph -was taken for the details of the pressure -trace over a period. of six or nine crank angles only during t;he i.gnition delay and. the rapid pressure rise per1iodls The gas pressure at any crank angle was calculated. from these traces by a s —atist ical adjustment of the values obtained from the sequenee of pressure

traces and. that from the trace for the whole cycle. The statistically adjusted values were used to plot the pressure trace for the whole cycle or any part of it by the computer. A sample trace for the pressure trace plotted by the computer for.the engine running on CITE fuel is shown in Fig. 6. The points shown on this trace correspond, to the reference points on the pressure trace taken for the whole cycle. The corresponding traces plotted. by the computer for the needle lift and. fuel pressure are shown in Fig. 7o It shows that the needle lift started. at 20.~3 before T.D.C., when the fuel pressure was 3650 psia. The fuel pressure reached a maximum value of 4200 psia at 18.3~ crank angles before T.D.C., while the needle lift was 2/1000 in. After this point the fuel pressure dropped. due to the discharge of the fuel into the cylinder. The maximum needle lift was 15o3/1000 in., at an angle of 1355~ before T.D.C. The needle was completely closed., at zero lift, at an angle of 74~0 before ToD.C. At this crank angle the fuel pressure was about 1550 psia. The fluctuations in the needle lift trace after its closure are due to the bouncing of the needle on its seat. The theoretical rate of fuel injection was calculated from the equivalent area for fuel flow, the difference between the fuel and. gas pressures. The coefficient of discharge was assumed, constant-during the injection period and, was computed from the ratio of the actual fuel consumption and, the theoretical accummulated. fuel. The equivalent area for fuel flow was calculated. from the needle seat area and, the holes area, as shown plotted. in Fig. 23 and, tabulated in Table 4. The rate of fuel injection, the accummulated fuel injection, and. the percentage of injected. fuel are shown plotted. by the computer in Fig. 8. The maximum rate of fuel injection was 370 lb per hour at an angle of 15.5~ before T.D.C. At this location only 32% of the total fuel injection was accummulated. in the cylind.er. When the needle was first closed., 95% of the fuel was injected into the cylind.er. This means that the after injection amounted to 4% of the total fuel. In this test the end. of the pressure rise delay was at 4.50 before ToD.C. after almost all the fuel has been injected into the cylind.er. The total amount of fuel injected. per cycle is 79~5 x 10m6 lbm. The detailed pressure trace during the ignition delay and the rest of the combustion process is shown in Fig. 9. The pressure fluctuations in this trace, near the maximum pressure, were smoothed. by taking their averages, and. used. for the heat release computations. The heat release diagram calculated for this cycle is shown in Fig. 10. This figure shows that the preignition reactions occur in two distinct stages: 1. The first stage from the start of injection at 20,35 before T.D.C. to 6~ before T. D C. During this stage negative heat release occurs and, is believed. to be due to the fuel evaporation and. the endothermic reactionso

1300 1200 I 100 1000 LLJ u) LL_ 0 -I) (I) C] bJ 900k 800k 700k 600k Ir n7 ATAC-I ENGINE OPEN COMBUSTION CHAMBER NATURALLY ASPIRATED FUEL = CITE SPEED= 2000 R.P.M F/A =0.03 I,- ~ ~ I - - - I ii I i i i i i i I 500k 400k 300 200k 100k (l 210 180 150 120 90 60 30 0 CRANK ANGLE -30 -60 -90 -120 -150 -180 DEGREES B.TD.C. -210 Fig. 6. Pressure trace for ATAC-1 engine plotted by the computer.

n Lo rn (f) l_ LLO U 0 0 0 C) I LL LJ Ld LUL z RI) 20 18 16 14 12 10 8 6 4 CRANK ANGLE DEGREES 2 0 -2 -4 Fig. 7. Fuel pressure and needle lift traces for ATAC-1 engine plotted by the computer.

I00 0 0 90 o rn 80 _ 70o or) z 60 o LL0 F50Z) 40 a 3< 20 0 R) 100 90Z 0 8Ld 80 w e, 70z 60 o LLJ 50 z 40 o 30 20 10 0 20 18 16 14 12 10 8 CRANK ANGLE 6 4 2 0 -2 -4 DEGREES B. T. D. C Fig. 8. Rate and computer. accumulated fuel injection for ATAC-1 engine plotted by the

1200 I100 I1000 LLJ J 900/ C0 -r | I ATAC-I ENGINE n 800- OPEN COMBUSTION CHAMBER z NATURALLY ASPIRATED,-.. / FUEL = CITE SPEED - 2000 R.R M ~~~~~~~700 XF/A =-0.03 08 6 4 2 0 -2 -4 -6 -8 -10 -12 -14 -16 -18 -20 CRANK ANGLE DEGREES B.T.D.C. Fig. 9. Detailed pressure trace for ATAC-1 engine during combustion.

.280 — r I.. ~ ----.2401 Lw.200 i D.160 a: LUJ j.080 Ll H.040 LLJ I uL.000 0 LU - -.040 0a: ATAC-I ENGINE OPEN COMBUSTION CHAMBER NATURALLY ASPIRATED FUEL = CITE SPEED = 2000 R.P. M F/A = 0.03 1=t I kC N) \id Ft IjC -- 0* 0 LL. Q: 11) 0 IC,) a. C0 -.080F z w -. I 2 V ---.~- _ L, I.. _... —....... __..._. -1 _ 24 21 18 15 12 9 6 3 0 CRANK ANGLE DEGREES -3 B.T D.C. -6 -9 -12 -15 -18 Fig. 10. Heat release diagram for ATAC engine with CITE fuel plotted by the computer.

2. The second stage is from 60 B.ToDoC. to 45~0 BQT.D.C., diuring which very slow reactions occur resulting in a small rate of heat release. These slow reactions are followed, by explosive type reactions, resulting in a maximum rate of heat release of 0.28 Btu per crank degree. It is interesting to note that the ignition delay period was 15.8~, while the following rapid combustion process lasted only for about 4.50. The two stage preignition reactions were also observed in the heat release diagram for diesel no. 2 fuel shown in Fig. 11. In this case the ignition delay was shorter and. the maximum rate of heat release was 0.21 Btu per crank degree, or 75% that of CITE fuel. The two stage preignition reactions in the combustion of hydrocarbon fuels were observed by other investigators as Jost,2 Andreev, 3 and Aivagov and Neumann. 4 COMPUTER PROGRAMS MADE FOR THE HEAT RELEASE CALCULATIONS The following computer programs were used for the cycle analysis and. heat release computations made for the ATAC engine. Program No. 1: Program No. 2: Program Noo 3: Program No. 4: Program No. 5: Program No. 6: Program No. 7: Heat release calculations Sequencial cycle data analysis Curve fitting Cylinder volume and gradient Cylinder gas properties Engine data reading and printing Engine data calculations The detail of each of these programs is given in Appendix A. _jV

.280.240 ci LLJ co Lr LLJ I LL 0 LUI HE.200.160.120.080.040 z - 0 C.) w z La. - 0 (I) ATAC-I ENGINE OPEN COMBUSTION CHAMBER NATURALLY ASPIRATED FUEL= DIESEL a. SPEED = 2000 R. P. M F/A - 0.03 LaL_ 0 z T _____ _____ _____ _________w o LO Cg Cg -0 \j,' H D C) I.000 1 --- —-- -.040 -.060 -.120 Cn in C)..-15 - -15 -18 24 21 18 15 12 9 6 3 0 -3 -6 CRANKANGLE DEGREES B.T D.C -9 -12 Fig. 11. Heat release diagram for ATAC engine with diesel no. 2 fuel plotted by the computer.

IIIL EFFECT OF SPEED ON IGNITION DELAY AND OTHER COMBUSTION PHENOMENA To study the effect of speed. on ignition delay and the other combustion phenomena, two series of runs were made, covering a speed range from 1000 rpm to 2900 rpmo One of these series was at a mean pressure of 500 psia and the other at 700 psiao The change in engine speed. was found. to cause changes in other parameters that affect the combustion process, like cylinder pressure and temperature, and injection timing. To study the effect of speed. alone on the combustion phenomena, experimental adjustments were made to eliminate the effect of these parameters or to correct for their effect on ignition delay. The injection timing was manually ad~justed so that the needle lift would start at a constant crank angle before the T.D.C., at all engine speed.s. The mean cylinder pressure during the ignition delay was kept at a constant value of 500 psia or 700 psia, by changing the pressure in the surge tank. The effect of the change in the mean temperature during the ignition delay was corrected for by using a correction formula based on the previous experimental results on the ATAC engine, with the same fuel under the same mean pressure'during the ignition delay. Al. EFFECT OF SPEED ON I.Dop AT MEAN PRESSURE = 500 psia Conditions of Test Fuel: CITE refree grade (Mil-F-45121 fuel) Mean pressure during IoD.p = 500 psia Inlet air temperature = 80~F Fuel-air ratio = 0.0315 Injector opening pressure = 3000 psia Injection timing (start of needle lift) = 20.9~ B.ToD.C. Cooling water at outlet = 176~F Variables Engine speed.: from 1000 to 2800 rpm Inlet air surge tank pressure: from barometric to 10.7 in. Hg boost 32

Results The effect of speed. on ignition delay is shown in Fig. 12. The measured. pressure rise delay I.D.p decreased from 1.567 millisec at 1000 rpm to l.149 millisec at 2800 rpm0 The illumination delay I.D.lL was always longer than the pressure rise delay, and decreased from 1.883 millisec at 1000 rpm, to 1.525 millisec at 2800 rpm. Under the test conditions the observed. change in ignition delay with engine speed. is due to variations in air velocity and. air temperature. To eliminate the effect of the change in the air temperature on ignition delay, a correction formula based. on Arrhenius equation was used.. I.D [ (T T corrected u ref. m = e (1) IoD. measured. where E = activation energy R = universal gas constant u T = a reference temperature to which the ignition delay is corrected. reo = 1619~ TM = the mean temperature during ignition delay. The value of the activation energy E was determined for CITE fuel under a mean pressure of 700 psia, and found equal to 10430 Btu/lb mole. The details of this work is given in Ref. 1. Upon using this value of E in Eq. (1), it was noticed that the corrected ignition delay increased with speed as shown in Fig. 135 Since this result seemed.to be contrary to previously published data for the effect of speed on ignition delay, it was decided to repeat this series of runs with a mean pressure during the ignition delay at 700 psia, the pressure at which the activation energy was determined. A2. EFFECT OF SPEED ON I. D. p, MEAN PRESSURE - 700 psia Conditions as in Al, except that the mean pressure during I.D.p = 700 psia. Variables Engine speed: from 1000 rpm to 2900 rpm Inlet surge tank pressure: from 22.9 in. Hgg to 10.6 Hgg. 33

1.9 1.8 1.7 Le )_J LlJ z 0 z (D 1.6 1.5 1.4 1.3 1.2 1.1 LLI z -..J (5 Li. 1000 2000 SPEED, RPM 3000 ENGINE Fig. 12. Effect of engine speed on ignition delay at a mean pressure of 500 psia. 34

1.8 1.7 C) Ln _J LLJ C z 0 z (5 LJ 0 C) 1.6 1.5 ATAC - I ENGINE F/A:.0315 Pmean: 500 PSIA Fuel: Cite Tintake: Ambient P intake: 10.7-0 In. Hg 0 0 1.4 1.3 1.2 I. I I I I I 1000 2000 SPEED, 3000 ENGINE RPM Fig. 13. Corrected ignition delay versus engine speed (reference temperature = 16190R). 35

Under the above conditions the mean temperature during the igni tion delay changed from 1436~R at 1000 rpm to 1707~R at 2900 rpm. The ignition delay was corrected for the change in temperature by using Eq. (1). The reference temperature, Tref, was chosen to be the mean temperature during the ignition delay at 2000 rpm which is equal to 1557~Ro Results Effect of speed on IoD.p. The results of the ignition delay in crank angle degrees and. in milliseconds are plotted versus engine speed in Fig. 14. The ignition delay is '72~ at 1000 rpm, and has increased. to 1l59o at 2900 rpm. Howiever, in terms of milliseconds, the ignition delay has dropped from 1.2 millisec at 1000 rpm, to 0.914 millisec at 2900 rpm. The drop in the ignition delay with the increase in speed. can be attributed to either the increase in turbulence with speed., or to the increase in the mean ~temperature during the ignition delay with speed.. The mean gas temperature, is shown in Fig. 15, increased from 1436~R at 1000 rpm, to 1707~R at 2900 rpmo This is an increase of 271~F. To correct for the effect of temperature on the ignition delay, Eq. (1) was used, and. the results are plotted in Fig. 14. These values'..of ignition delay can be considered to be at the same mean temperature and, pressure, and the only variable is the engine speed. From Fig. 14, it can be concluded that the increase in speed from 1000 rpm to 2900 rpm caused an increase in the ignition delay from 0.9 millisec to 1.23 mllisec. Similar observations concerning the increase in ignition delay with speed were reported, by Small.5 The reason for the increase in the ignition delay with speed may be attributed to the increased leanness of the fuel-air mixture, in the region where comb-ustion starts in the combustion chamber. Photographic studies on diesel combustion6'7,8 showed. that ignition starts in the pheriphery of the fuel spray, where the fuel droplets have access to the oxygen. The change in the mixture strength in this region is expect-ed t'o affect the rate of reaction between the oxygen and, fuel. Arn increase in engine speed. is expected, to reduce the physical delay, which is the time required for the fuel to evaporate and form a combustible mixture. So if the physical parameters are the main contrEolling factors in the length of the i.gnition delay, it would be expected. that an increase in engine speed would.reIuce the length of the ignition delay. However, the present experimental results show that the ignition delay increases with the speedO This might be an.indi.cation that the chemical processes, rather than the physical processes, are t`he main controlling factors on *the ignition delay. 36

ATAC OPEN CHAMBER ENGINE 1.50[ F/A:.0315 Pmean:700 PSIA Fuel: Cite Tcoolant: 170 F I. D. Corrected to Tmeaon=1557 o R 1.40H A. LLJ.111 LI z r', 0 (D 1.30 - /' b~~~~~~~o 16 15 18 19 17 ct, Lu -J z C) 14 13 / I 1.101 - I 0 I 1.00 12 I LLI iiI c,. z 0 o 9z 8 7 6 5.90 I I I rooo 2000 ENGINE SPEED, RPM 3000 Fig. 14. Effect of engine speed on ignition delay at a mean 700 psia. pressure of 37

0 IJ LLJ (.9 z L< cn I 1700 - 1600 ATAC OPEN CHAMBER ENGINE F/A:.0315 Pmean: 700 PSIA Fuel: Cite Tcoolant: 170'F 1500 - 1400 I I I 1000 2000 3000 ENGINE SPEED, RPM Fig. 15. Effect of speed on the mean gas temperature during the ignition delay.

B o EFFECT OF SPEED ON SMOKE INTENSITY The results of smoke intensity in Hartridge Units are plotted versus engine speed in Fig. 16. Below 1500 rpm, there is one data point at 1000 rpm, which shows a heavy smoke intensity reading. The trend. of change in smoke intensity between 1000 rpm to 1500 rpm cannot be concluded. from the data point at 1000 rpm. But between 1500 rpm and 2900 rpm, the smoke intensity is shown to increase with speed. The increase in speed. is expected to improve the mixing between the fuel and air, and. increase the combustion efficiencyo However, at higher speeds the time available for the chemical reactions to take place, at a certain temperature level, is reduced. Thus the carbon particles formed. during the combustion process will have a shorter residence time, at the temperature below which they cannot combine with the oxygen. From these experimental results it seems that the process of mixing is not the controlling process for carbon formation, but rather the temperature level and time available for the chemical reactions to take place are the main factors that affect carbon formation and. removal, and. thus the smoke intensity in the exhaust. C. EFFECT OF SPEED ON COMBUSTION CHAMBER WALL TEMPERATURES The wall temperatures are measured. in the fire deck at three different locations: 1. The surface of the combustion chamber in the midpoint between the inlet and. exhaust valves. 2. The wall temperature at a radial distance of 1/8 in. from the inlet valve insert, and 1/4 in. from the gas side. 3. The wall temperature at a radial distance of 1/8 in. from the exhaust valve insert, and. 1/4 in. from the gas side. The temperature of the fire-deck wall, at the three different locations, is plotted versus engine speed in Fig. 17o The surface temperature in the valves bridge increased. from 4350F at 1000 rpm to 509~F at 2900 rpm. The increase in surface temperature occurred between 1000 rpm and. 2000 rpm, and was very little between 2000 rpm and. 2900 rpm. The wall temperature near the exhaust valve increased. from 5260F at 1000 rpm to 360~F at 2900 rpmo The wall temperature near the inlet valve was almost constant all over the whole speed. range, at about 2670F. 39

ATAC OPEN CHAMBER ENGINE 80 80 F/A:.0315 Pmean: 700 PSIA s( loFuel: Cite 19 70 Tmcoolant:170~0F c 60 LLU u 50 0 () 40 1000 2000 3000 ENGINE SPEED, RPM Fig. 16. Effect of speed on smoke intensity. 40

n IL IJ 300 50 U< 40 r 30 rr LLU c20 3000 > 3000 o z (.) LU QZ LLJ LL H 200 L — 1000 1500 2000 ENGINE SPEED, 2500 RPM Fig. 17. Effect of engine speed on wall temperature. 41

The swing in the surface temperature decreased from 370F at 1000 rpm to i3~F at 2900 rpm. It is to be noted. that all the above variations in temperature occurred. with *the following parameters kept at a constant value: fuel-air ratio, coolant temperature, injection opening pressure and. timing, mean pressure during delay, and. inlet air temperature. Thus the changes in the wall temperatures can be attributed. only to changes in the heat transfer phenomena associated. with engine speed o D. EFFECT OF SPEED ON THERMAL LOADING The heat lost from the gases to the combustion chamber walls, is transferred. to the jackets cooling water or to the lubricating oil heat exchanger. Figure 18 shows that the heat lost to the water jackets increased slightly from 4e0 Btu/sec at 1000 rpm to 401 Btu/sec at 2900 rpm, and reached. a maximum of 5.8 BtBu/sec at 2500 rpm. The heat lost to the lubricating oil was 0.5 Btu/sec over a speed. range from 1000 rpm to 2000 rpm, after which it increased. gradually till it reached. 2.8 Btu/sec, at 2900 rpm. The sum of the heat lost to the coolant and. lubricating oil showed a continuous increase with speed. The thermal loading as a percentage of the heat added. in the fuel is plotted in Fig. 18. It shows an increasing trend. in the percentage heat lost 'to the lubricating oil with speed. The percentage heat lost to the coolant and the total losses showed. a continuous decrease with speed. About 20% of the heating value of the fuel is lost at 1000 rpm and. it decreases to 14% at 2900 rpmo The results of this series of runs are shown tabulated by computer in Appendix B, Tables 1 and, 2. 42

8.0 C) U (I) N -J _J I H 7.0 6.0 5.0 4.0 3.0 2.0 1.0 o\e 0% 0 I LJLLJ I I - 3000 cr 3000 1500 3000 ENGINE SPEED, 2500 RPM Fig. 18. Effect of engine speed on thermal loading.

IVo EFFECT OF COOLANT TEMPERATURE ON IGNITION DELAY AND OTHER COMBUSTION PHENOMENA This series of tests was run to study the effect of coolant temperature on the combustion process in the ATAC engine, in an effort to evaluate the possibility of running coolant systems at temperatures higher than the present temperature levels of about 2000~F The increase in the coolant temperature results in an increase in the temperature differential between the coolant and. air, and. reduce the size of the radiator for a certain cooling load. At the present time, it seems that the radiator size might limit the increase in power output of diesel engines, specially in some military applications. In the present experimental study the thermal loading was measured, and the coolant used. was "ethylene glycol", The tests covered a range of coolant temperatures from 1500F to 3000Fo The temperature of the lubricating oil in the crankcase was kept at a constant level of 2000F. This limitation was made to avoid. any trouble that might occur due to the increase in the lubricating oil temperature. Conditions of the Test Fuel - CITE refree grade (Mil-F-45121) Pressure in surge tanks = barometric Inlet air temperature = 81~F Fuel-air ratio = 0.0313 Injector opening pressure = 3000 psia Injector timing (start of needle lift) = 21~ B.T.D.C. Lubricating oil temperature = 200~F Engine speed. = 2000 rpm Variables Outlet coolant temperature: 156~F-305~F Results The results for the effect of coolant temperature on the different combustion phenomena are given in Table 3 in Appendix B. 44

A. EFFECT OF COOLANT TEMPERATURE ON COMBUSTION PHENOMENA The pressure rise delay did not change with the increase in coolant temperatureo The average value for the ignition delay for seven runs was 0.681 s sec, the maximum ignition delay was 0.709; or 4% above the average. The minimum ignition delay was 0.667; or 2% below the average. These changes in ignition delays can be considered as random changes. The experimental results showed no effect for the coolant temperature upon the compression pressure, maximum cycle pressure and rate of pressure rise. The exhaust gas temperature increased. with the coolant temperature. At a coolant temperature of 156~F the exhaust temperature was 846~F, and. increased. to 950~F at coolant temperature of 305~F. B. EFFECT OF COOLANT TEMPERATURE ON THERMAL LOAD The thermal load, can be considered. to be composed of heat losses to the coolant, and, heat losses to the lubricating oil. The variation in these heat losses with coolant temperatures in shown in Fig. 19. The increase in temperature from 156. 6F to 305'F reduced the total thermal loading from 30,600 Btu/hr to about 20,500 Btu/hr. This is mainly duii-to the reduction in the temperature difference between the gases and the walls. The corresponding thermal loading as a percentage of the power output is 1660 Btu/B.H.P. hr and 1240 Btu/H.P. hr respectively. The percentage heat loss to the coolant, shown in Fig. 20, decreased from 15.3% at 156~F, to 8.4% at 305~F. For the lubricating oil the percentage heat losses increased from 2.4% at 156~F to 5[4% at 305~F. The percentage total heat losses to the coolant and. the lubricating oil decreased from 17.7% at 1560F to 13.8% at 305~F. C. EFFECT OF COOLANT TEMPERATURE ON INJECTION PROCESS No effect was observed. for the coolant temperature on injection timing, the period. of main injection or the period. of after injection. The only effect on the injection system was observed. in the amount of after injection. The needle lift during after injection shown in Fig. 21 was observed. to d.ecrease with the increase in coolant temperature up to 230~F, after which it increased again. Figure 22 shows the needle lift diagrams at coolant temperatures of 217~F and. 304-3~F. It is noticed. that at the higher temperature the needle lift, was approximately twice as much as that at the lower temperature. 45

A 1700 o: 1600 ra 41500 nr c 1400 LI 0 < 1300 ~ 12001 a::1 I 1%, I ATAC OPEN CHAMBER ENGINE Speed: 2000 RPM B.M.E.P.: 100 PSI Coolant: Ethylene Glycol \] z Lub. Oil Temp.: 200~F (Constant) 30,000 28,000 26,000 24,000 22,000 20,000 <9 b — -I ON -- I I I I I I I I I I0 I I I I I I I I I I I I II 150 200 COOLANT 250 TEMPERATURE, ~F 300 Fig. 19. Effect of coolant temperature on thermal loading.

20 m 15 cn (n C> 0 F — LLuJ CL C, Lu A ATAC OPEN CHAMBER ENGINE Speed: 2000 RPM * a _ E f O a I10 5 a B.M.I...: IUU P5I Coolant: Ethylene Glycol Lub. Oil Temp.: 2000F (Constant) I Lu _rl j 0 I I I I I I 50 200 250 COOLANT TEMPERATURE,OF 300 Fig. 20. Effect of coolant temperature or- >7o heat lost to coolant and lubricating oil. 47

_ I I I I 0 0 0 Nzz 0 C) LU z r 12 LLU 8 LL 6 _I ATAC OPEN CHAMBER ENGINE Speed: B.M.E.P. Coolont Lub. Oil 2000 RPM: 100 psi: Ethylene Glycol Temp.: 2000F (constant) LU -J LU z W~ W: 0 0 4 2 01 15 I I I I I I I I I I I I I I I I Ii I I I I I I II f ' I i. I I I I i0 200 COOLANT 250 TEMPERATURE OF 300 Fig. 21. Effect of coolant temperature on needle lift during after injection. 48

(a) Coolant temperature = 217~F (b) Coolant temperature = 304.3~F 22. Needle lift diagrams with coolant temperatures of 2170F and 304.30F. 49

V. PISTON AND LINER INSPECTION AFTER THE HIGH COOLANT TEMPERATURE TESTS To check the condition of piston, liner and. valve seats after the completion of the high coolant temperature tests, the cylinder head was removed. The liner, piston and. valves were examined and found in a fair condition without any sign of overheating. The piston rings and. valves were replaced with new ones. The new valves were lapped. on the seats. 50

APPENDIX A COMPUTER PROGRAMS 1L MAIN COMPUTER PROGRAMS These computer programs are written in the Michigan Algorithm Decoder (MAD) language which is the language used at The University of Michigan Computing Center. Program 1. Heat Release Calculations 2. Sequential Cycle Data Analysis 3. Engine Data Reading and. Printing (ENGDAT) 4. Engine Data Calculations (ENGCAL) 5. Fuel Injection System Analysis 6. Equivalent Area of Injection as a Function of Injector-Needle Lift (AREAS 7. Integration of Given Data (INTDER) 8. Best Straight Line to Fit a Group of Points (BLINE) 9. Curve Fitting (DB4Tll) 10. Cylinder Volume and Gradient (CYLVOL, CYLGRA) 11. Cylinder Gas Properties (BBCFAC, BBRAN, BBFAR, BBLFT3) 12. Title Printing (TITLE) 13. Fuel Properties (FULHCR, FULDEN, FULFLO) 14. Coolant and Oil Properties (COLID, OILID, COLDEN, OILDEN, COLCP, OILCP, ) 15. 16. COLNU) Calculation of the Integral Mean Value of Given Data (MEAN) Interpolation (INTERP) 51

17. Air Flow Rate (AIRFLO) 18. Average Values and Errors (AVEERR) 19. Cylinder Wall Temperature from Millivolt Read.ings (THERMO) 20. Check on Missing Data (LACK) 21. Rounding of Numbers (IROUND) 2. DATA PLOTTING ROUTINES Program 22. Axes Plotting (AXIS) 23. Curve Plotting (GRAPH) 24. Results Punching (PUNCH) 52

Computer Program 1 Title: Heat Release Calculations Purpose: To calculate the net heat release from the combustion reactions over a range of crank angles starting from the point of injection to near the end. of the combustion process. Input: 1. Cylinder pressure obtained and punched. from the program, "Sequencial Cycle Data Analysis" 2. Engine test data Procedure: 1. Read cylinder pressure, from the program, "Sequencial Cycle Data Analysist, program 2. 2. Interpolate and. determine the pressure every one-eighth of a crank-angle d.egree. 35 Calculate the mass of the charge in the cylinder by using the program "'ENGCAL", program 4. 4. Calculate the average temperature of the gases from their pressure, volume, and mass, by using the "Beattie-Bridgeman" equation of state. The subroutine used. for these calculations is given in program no. 11. 5. Calculate the rate of change of temperature (d.T/de), w.r.t. the crank angles, by using the program 9. 6. Calculate the volume gradient:(dV/de) by using the program 10. 7- Calculate the rate of doing work at any crank angle 6, 5w -4 dV = 1.07116 x 10 x -- 56 d. where d.V/dO is the change in cylinder volume w.r.t. the crank angles. 8. Calculate the change of the internal energy, dU, by using the following equation: 53

dU dT - = Mx c x d d.e v dE where c is the specific heat at constant volume, V (7864 36.1 2387 + 905000 c = (7864 T -T T+ ) 9. Calculate the rate of heat release from &Q _d.U +w bE dE b8 where Q is heat transfer List of Assisting Subroutines: 1. Program to calculate the mass of the charge and the fuel-air ratio (name: ENGCAL) program 4. 2. Program to calculate the hydrogen to carbon ratio of the fuel (name: FULHCR) program 13. 35 Program to round. out numbers (name: I ROUND) program 21. 4. Program for interpolation (name: INTERP) program 16. 5. Program to calculate the temperature in degrees Rankine (name: BBRAN) program 11. 6. Program to calculate the temperature gradient (name: DB4Tll) program 9. 7- Program to calculate the cylinder volume gradient (CYLGRA) program 10. 8. Program to punch the results (PUNCH) program 24. 9. Library ploting subroutines (PLTPAP., PLTMAX, PLTOFS., PLINE., PLTEND).

Computer Program 1 Heat Release Calculations D'N SPEC(18), ID(3), DATA(21), CALC(20)t i (.DUIUL, CP, ' TI W, - llW, u1I, Si"URtI, D()L)(1U24) I'R IROUND., NUMDAT, ENDDAT, NUMSEQ, ENDSEO, I AGAIN EWNGCAL. ( 1, SPECC iuD( ), DAA( ),CALC( 1 - GAS = CALC(5) + CALC(7) RGAS-= (CALC(5)*.371110 + CALC(7)*(.371110 + CALC(4)/ 1 (.3757 + 4.4769/FULHCR.(SPEC(4))))/(1 + CALC(4)))/GAS DLU = GAS/28.966 GAS = GAS*1728. R'T $S15,F16.10S5,F16.10, S7, F16. 10*$ BEGIN, EVERY, END NUMDAT = 1 + IROUND.((END-BEGIN)/EVERY) ENDDAT = 1 + 8*NUMDAT NUMSEO = ENDDAT - 8 tENDSt( = NUMSEO + 1 DELSEO = EVERY/8. DBTDC- = BEGTN - DELSEO (I = 1, 1, I.E. ENDSEO, 1 DBTDC(I ) = DBTIDC + I*Lt-LSEQ, 2 DBTDC(I) = 0. + DBTDC(I)). R'I $S10,10f.-(.3'$, (I = 1, 8, I.t. ENDDAT, CP(I)) INTERP.(NUMDAT,DBTDC(1),8,CP(1)) DW = 1./.3676/14.696/1728. T'H LOOPi, FOR I = i, 1, I.E. ENDSEO DBlTDC = DBTDC(TTICP = CP(I) T = BtiRAN. ( CP,GAS/CYLVUL. ( DB )C ) AS ) T(I) = T J- [L)W(i) = 1.071 i-6-4"CP'CYLGRA. (UBT-DC) LOOPL DtJ(I) = DU*(7.864 - 36.1/SORT.(T) - 2387./T + 905000./T/T) DB4 Ii.11. (NUMS EO,-DESEL,T,( 1 ),Si SRE(1 ), DI( 1 ) STORE(1),STORE(),STOR E(l1)) I'H LUUP2, FUR I = i, 1, I.E. ENDSEO DU(i) = DU(I)*DT(I) LOOP2 DQ(IT = DW(I) + DU( 1) READ DATA P'T $ ( H/lHO54(/F10.4,2 F10. 1,3P4F. 2) ) $, (I = 1, 1, I.E. ENDSEO, Z H I )DC(I), CP( I ), 1( I), DWI ), DU(I), DO(I), 3 D( I )*EXP. ( SLOPE/T(I))) PUI\CH ( I D( 1),$DQ $, 1,NUMSEO,,D( 1 ) ) PLTPAP. ( $400$ ) PL TXMX. (14.90) PLTOFS. (21.,-2.*,-2,.06666666667,.65,.41) PL INEt. I( [) ( I 1)!]ID( 1 ) t NUMS t:, 10), O, 1. ) PLTEND. T O A-GA I N E'M 55

Computer Program 2 Title: Sequencial Cycle Data Analysis Purpose: To determine the cylinder pressure during the cycle from the time of inlet valve closing to the exhaust valve opening. Input: Data points measured. from a group of traces taken for different intervals during the cycle from the inlet valve closing to exhaust valve opening. Procedure: 1. Read. a sequence of data points as indicated under "Input". 2. Statistically adjust the data giving adjusted values, errors, deviations, and probabilities. 3. Curve fit the adjusted. values by applying a fourth degree polynomial curve through eleven consecutive points. The program for this step is known as DB4Tll program. 4. Print, punch or plot the results. List of Assisting Subroutines: 1. Program to print the title (name: TITLE) program 12. 2. Program to curve fit the adjusted values (name: DB4Tll) program 9. 3. Program to use the program in (2), for the required number of times and for interpolation (USEDB4, INTERP) program 16. 4. Program to calculate cylinder well temperature from milivolt readings of traces (THERMO) program 19. 5 Punching, plotting and, graphing programs (PLOT, GRAPH, PUNCH) program 23 and. 240 NOTE: This program was used to calculate cylinder gas pressure as shown in Fig. 6. 56

Computer Program 2 Sequential Cycle Data Analysis,XTSET DHOTOS D'N CM(1689), (DBTDC, DATA, BEST)(1.441), (COMMON, ERRCOM) J, (49R),.(MVCM, *CM'REF, ERRREF, UNITCM, BTDC, REF, REFERR, 2 l _0, RLOERR, ADJ, ADJERR)(250), SPEC(19), YTITLE(117), 3 HEAD(16), VALUJES(7), SCALES(5), NUMBER(3 ) EQUIII\VALENCE ( TDC, UINITCMI), (BEST, REFERR), 1 (REST(251), RLO), (BEST(502), BLOERR), (BEST(753.), ADJ), 2 ((REST.(1004), ADJERR) I'R TITLE., LII\NE, NUMBER, Pt COMMON, BGN? END, LAST? OBSt FV? 1 I I, I 3, LINES, SPEC, NIJMDAT, YTITLE, HAD, IROUND., DEL, 2 RCB, N i. R'N EXACT, DOPLOT, DOGRPH, ODUoREAD, DOPRNIT, DOPNCH, DOTELL, D I DOR4, t WT F' E FV LINE = TITLE.(i1,SPEC) READ DATA SPACE. (L INIE, 6, 24) P'T $1OH-DA-TA SFT C4,9H RUN Ji' C4, 1 5H RESUILTS SET C4,4H HA 1ST4,23H PHOTOS (SCALE FACTOR =F].1.6,30H JUNITS/MV); DATA TAKE 2\1 o EACHFP.2,?H I)RTFOC.-'$, 3 ' SPEC...SPEC(2), l2,NUNlkJER, VALUES,, VALLUES(2) LIN I TCM ( 1 ) = VA Lt.IES;''\v C ( 1) ZERlO. (COMMONi\l,EINIR.EF( 1 ),?BIO( 1)) BTDC(1') - VA61IJES(1) REFERR = NITC(1))*ERRREF((1) ) REFRR(.1) = REFERR'REFERR RLOERR(1) = REFERR(1) T'H PHOTOS, FOR P = 2, 1, P.G. \UMBER JN I TCM = VA L lU F S,-' M VC,l; ( P UNIITC ( P) = UN I TCiv ' COIVIMOrN' = COMMONiI +. BGN = COMMIiN ( COMilrON\ ) W' R RGN.,.NE. END + 1, ERROR. B NI\ ER R = N. \l TC T,'*E E RRC E M ( C n1l M MO N\ ) COMMON = COivlMM!UN + 1 END = CO iOON!n ( COMIM'tON ) ~ENDERR = U. I TCMI*ERRCOMV1( COM) N\ ) LAST = P - 1 RTDC(P) = BTDC(LAST) + (END- BGI\N) VALUES (2) REF ( P) = UNITCM ( 1 )(CREF(P) - CMREF ( 1 ) ) REFERR = UNITCM( 1)*ERRREF(P) REFERR(P) = REFERR",'REFERR RLO(P) = BLO(LAST) + I.IIJNTC.M,(CM (END) - CIM(BGN)) RLOERR( P) = RLOERR('LAST) + ENDERRE.ENDERR + BGNERR*,BGNERR TtH ADJUST, FOR P = 1, 1, P.G. NUMBER EXACT = ORF ADJ = O. ADJERR = 0. T'H OBSERV\/ FOR ORS = 1, 1, OBS.G.. NUMBER NUMIER = REF (DOBS) + BLI:(P) - BLO(OBS) DExlNOM = REFERR(OBS) +.ABS. (BLOERR(P) - BLOERR(OBS)-) W'R DENOM.E. O. W'R EXACT W'R.ABS. ((ADJ - NUMER)/UNITCM (P)) G...005, ERROR..'0 E EXACT = lB ADJ = NUMER ADJ( P) = NUMER ADJERR(P) = 0. E I L 57

Computer Program 2 (Continued) FlR,l'NT. FXACT AI),l = Qa1)J + I\lI.JMER/DENOM AJF)IERR = ADJFRR +../DENOMI F '! W1IR.NOT. EXACT ADJ(P) = ADJ/ADJERR An,]FRR(P) = 1./ADJERR F' L A DJi.U)sT, 'E P'T T OP \/'S TOP = $1.32H01 —SEOIIJENTIAL PHOTO ANALYSIS DATA (A1 = REFER IENCE FOR SEQtJENTIAL BLDWUJPS) —I PERCENT -REFERENCE 2 RIil L(JPS ADdJI.ISTMllENTS/104H PHO MV/CM DBTDC ON 1 ERR SEO 31.FNTIAL CENTIMETER MEASUtREMENTS ON THE BLOWtJPS. PROBAB FACTOR 4 IlINITTS FRR2 ( 14H U.JITS FRR )*$ P'T.H 1 F9.3':-'$. MVCM( 1) P= F\/ = 5 - NI.JMBER( 1) PO INT. LINF = LINE + 8 COMMON = 0 I =. J = 1. DA4T(1) = ADJ(1) T'H PRINT, FOR P = 2, 1, P.G. NUMBER COMMON = COMMON + 1 BGl = COMMON ( COMMON) RGINERR = ERRCOM(COMMON) COMMON = COMMON + 1 END = COMMON(COMMON) LINES = 4 + (END - BGN)/10 L INE = LINE + LINES W'R LINE.G. 60 PIT $1H1/lH-/lHOY$ P'T TOP LINE = 12 + LINES E'L LAST = P - 1 ADJ = ADJ(P) - ADnJ(LAST) RLO = BILO(P) - BLO(LAST-) FACTOR = ADJ/BLO l. NITCM = FACTOR*UNITCM(P) DATA = ADJ(LAST) - UNITCM*CM(BGN) (I = I + 1, 1, I.G. END, 1 J = J + NUMBER(3), 2 DATA(J) = DATA + UJNITCM*CM(I)) P' T $F27.2/I4,F9.3,S65,F6.2,F8.3*$, 1 BGNERR, Pt M\VCM(P), 2 100.*(1. - ERF.(.ABS.(BLO - ADJ)/SORT.(2.*( 3 BLOERR(P) - BLOERR(LAST) + ADJERR(P) + ADJERR(LAST))))), 4 100."(FACTOR - 1.) W'R LINES.E. 4 P'T $1H+S26,10F5.2*$, CM(BGN)...CM(END) O'F P'T $1H+S26, 1OF5.2/ ( S27, 10F5.2 )*$, CM( BGN)...CM( END) E'L PIT $F27.2 *'$, ERRCOM(COMMON) PR I KNT POIN [T. DOPIOT = SPEC(3).E. $PLOT$ 58

Computer Program 2.Sequential Cycle Data Analysis NXTSET PHOTOS D'N1 CMv(1689), (DBTDC, DATA, BEST) (441), (COMMON, ERRCOM) 1 (498), (M\/CM, CMREF, ERRREF, UNITCM, BTDC, REF, REFERR, 2 RLO, RL.OERR, ADJ, ADJERR)(250), SPEC(19), YTITLE( 17)-, 3 HEAD(16), \/ALUES(7), SCALES(5), NUMBER(3) EO.II \/ALENCE ( C)DbTC, (I..)NITCM), (BEST, REFERR), I (REST(251), BLO), (BEST(502), BLOERR), (BEST(753.), ADJ), 2.(REST.(1004), ADJERR) I 'R TITLE., LINfE, NIJUMBER, P, COMMON,.BGN, END, LAST? OBS, FV, 1 IT, IJ, LI.NES, SPEC, NWIMDAT, YTITLE, H-AD, IROUND., DEL, 2 KC DBiN. R'N EXACT, DOPLOT, DOGRPH, D[)[OREAD, DOPRNT, DOPNCH, DOTELL,.DIDORA4, WT F 'E F\/ LINE = TITL E.(],SPEC) RFAD DATA SPACE. (LIINE,6,24) P'T l1OH-DATA.SFT C4,9H: RKIJiR # C4,15H: RESULTS SET C4,4H HA ]ST4,23H PHOTOS (SCALE FACTOR =F11.6,30H UNITS/IMV); DATA TAKE 2T\1 ) EACHFP.2,6H I)BTDC;:'s, 3 SPEC...SPEC(2), \JER, VALUES, VALUES(2) LW I ITCM ( 1 ) = VALIE S'\I \!CM ( 1) ZERO. (COMION, EtD\l', DRFF( 1)BI_( 1)) BTD)C(1) = V\/ALES(1) REFERR = tJNITCM(1) *ERRREF(1) REFFRR(1) = REFFRR"'REFERR RLOEFRR(1) = REFERR(l) T'H PHOTOS, FOR P = 2, 1, P.. i\NUMBER tN I TC M =r \/AL I.JES:-MV\/C,J( P ) UJNI I TCM ( P ) = UN I TCi CONIvM[IN' = COMMONI + 1 BGN = COMMION(COMON) W'R BGN.NE. END + 1, ERROR. BGNERR =.ll I TC V,i,'ERRCFOM ( COMIvMON\ ) COMMON i = C OivllMU!i + 1 E ND = C ivi M ON ( CO o ivO ', h, ) lENDERR = U I ITCMvI*'"ERRCODM ( C()OMMON(J\ ) LAST = P - 1 - RTDC(P) = BTDC(LAST) + (END - BGN) VALUJES(2) RFF(P) = UNITCI'!(1)- (CMREF(P) - CMREF(1)) REFERR = lJN! I TCIMi ( 1 ) *PERRREF(P) REFERR(P) = REFERR*REFFFRR BLO(P) = BLO(LAST) + l)UNITC.M",f'l(CM(EtXND) - CM(BGN)) BLOERR(P) = RLOERR('LAST) + ENDERR*ENDERR + BGNERR*'.BGNERR T'H ADJUST, FOR P = 1, 1, P.G. NUMBER EXACT = OB ADJ - 0. ADJERR = 0. T'H ORSERV, FOR OBS = 1, 1, 0OS.G. NUMBER NIMIJiER = REF(OBS) + BLO(P) - BLO(OBS) DENOM = REFERR(OBS) +.ABS. (BLOERR(P) - BLOERR(OBS)) W'R DENO \M E. 0. W' R. EXACT W'R.ABS. ((ADJ - NUMER)/UNITCM(P)).G..005, ERROR. EXACT = iB ADJ = NUMER ADJ(P) = NUMER-' ADJERR(P)= 0.- FE I L 57

Computer Program 2 (Continued),Rl.NOT. EXACT AfI,l = ADJ + N\ltJlvlER/ ENlM.A!),IERR = A.I)ERR + l./DENO"lA F 'L C'E I!,IR.NOT. EXACT ADI(P) = ADJ/ADJERR A,.FRR(P) = 1./ADJERR AD l)JS T C ' E P'T TOP \'S TOP = $132HHO — SEOIJENTIAL PHOTO ANALYSIS DATA (#1 = REFER 1ENCE FOR SE0t!ENTIAL BLOWI)PS) —I PERCENT -REFERENCE 2 R lliJ P S ADJ I.ISTiM,/ENTS/104H PHO MV/CM DBTDC ONf 1 ERR SEO 311IFNTIAL CENTIMFETER MEAS(JREMENNTS O.)N THE BLOWUtPS. PROBAB FACTOR 4 IJNITS ERR2( 14H UNiITS F RR)*$ P' T +.H 1 F 9. 3".-$. MlVC M (1) P =. F\/ = 5 - NMBER( 1) POI NT. LINE = LINE + 8 COMMON = o = 1 DATA(1) = ADJ(1) T'H PRINT, FOR P = 2, 1, P.G. 'NtUMBER COMMON = COMMON + 1 BGN = COMMON(COMMON) RGNIERR = ERRCOM(COMMON) COMMON = COMMON + 1 END = COMMON(COMMON) I.INES = 4 + (END - BGN)/10 LINE = LINE + LINES W'R LINE.G. 60 P'T $lHl/lH-/H1H0: $ P'T TOP LINE = 12 + LINES E'L L AST = P - 1 ADJ = ADJ(P) - ADJ(LAST) BLO = BLO (P) - BLO(LAST') FACTOR = ADJ/BLO UJNITCM = FACTOR U.-'L NITCM(P) DATA = ADJ(LAST) - UNITCM*CM(BGN) (I = I + 1, 1, I.G. END, _ 1 = J + NUI.MBER(3), 2 DATA(J) = DATA + UNITCM*CM(I)) P'T $F27.2/I4,F9.3,S65,F6.2,F8.3*$, BGI\IERR, P, M\ICM(P), 2 100..".(1.- ERF.(.ABS.(BLO - ADJ)/SORT.(2.*( 3 BLOERR(P) - BLOERR(LAST) + ADJERR(P) + ADJERR(LAST))))), 4 100."(FACTOR - 1.) W'R LINES.E. 4 P'T $1H+S26,lOF5.2*$, CM(BGN)... CM(END) O'F P'IT $1H+S26, 1OF5.2/ ( S27, lOFS.2 )*$, CM( RGN)...CM( END) E'L P'T $F27,-2*$', ERRCOM(COMMON) PR I NT POI NT. DO PLOT = SPEC(3) E. $'PLOT$ 58

Computer Program 2 (Continued) D-IGRPH = 5PEC(4).E. $(RPH$ DF)READ = DOGRPH. OR. DOPLOT DOPRNT = SPFC(5).F. $PRNT$ FD)PNCH = SPEC (6). E $PI\ICH$ Df1TELL = D OPNCH ODR. DOPRNT W, '-R DOTELL.[R. DOREAD DELINT = VAIUES(2)/\UNRER (3) P'T $26H-DATA WILL BE CUIRVE FITTEDI2,23H TIMES, SHIFTEDI SO TH lATFR.,lOH DBTDC HASF10.4,20H t NITS, INTERPOILATEDI3,11H TO 1' 2(EACHF12.6,7H ) DBTD.C), 3 IIJMBR (2),: ALIJES(3) VAL JFS( 4 ), N\i.MBER (3), DLINT N\, JllviDAT = 1 + ( J - ] ) /i.!ltFR ( 3) D)RTOC(1.) = RT.DC(1) DRTDC = RTDC(1) - DELINT _ (I' = 1, 1, I.G. J. 1 )RTDC(I) = fRTDC + ID'F ELI NT) IS_ ED F 4. ( NUIMDAT, VALIE S ( 2 ), N1\UI. MBFR ( 3 ) DATA ( 1 ) BEST ( 1 ) 1.11l liviRE R ( 2 ), t.DDB4 ) D I DDf4 = 1k TERI = \IALI)S (-4) - TA.(V ALt.IES ( 3 ),)BTDC(].),BEST (1 ),NU\! BER(3), ]. ixl Ji FMBER ( 3 ), 5, 1JlU1DAT, 1. ) T'I SKIP n- i.! DI ODR4 ) = (R TERM = VLt LUES ( ). - TAB,( VALUJES ( 3 D),DB'TDC ( 1),DATA( 1 ), NUMBER ( 3 ), 1 3~\ I J t H f R ( 3 ) 5, IiER(3) 5 MDAT, 1.)!SKIP NIT = SPEC (?).RS. 24.E. $00. O..IT.T Ir.l R TERM.NE. 0. 1,I, R r":.1G R PH T'H SHIFTR, FOR P, 1, I P.. NUJMBER RFF(P) = REF(P) + TERM SHIFTR W1 R!.'T, RF(P) = THERf. (REF(P) ) F 'L T'H SHIFTIT, FOR I = 1, 1tIJMvER(3), I.G. J DQATA (I) = ')ATA ( I) + TERM wR DI)D)R4-, BEST(I) = BEST(I) + TERM w' R T DATA( I) = THERM). ( DATA(I) ) WrR DID)DR4, REST(I) = THERM). ( BEST(I)) SHIFTD E'L F 'I I NTF:R P. ( NJlvlhDAT T, TDC ( 1. ), N) BlER ( 3), )ATA ( 1 ) ).!W'R r) I)DB4, II'TFRP. ( MDAT DBTDC( 1), NU ER( 3 ), BEST( ) )!,R R) REA. DF XTITLE =.F45 XTI-I E( ) 2 3 \/V'S XTITLE(2) = $CRANKANG6LE DEGREES BTIDC$ R F. [) DATA I, R DO)PLfT W'J ' R. OTD FB4 )' E PLDT. (SCALES? XTITLEYT ITLEtHEADtJDBTDC 1),DATA( 1) ) F' L E'L 1,R DOR PH GRAPH. ( SCALES,XTITLE,YTITLE,HEAD) PLINE. (BTDC( 1 ),REF( 1),NUlBER, 1,-1l,,1. ) I = 1. +.06*.ABS.(SCALES ( 1 )/SCALES(2)/DELINIT) ~3 = 1 + (. -.1)/I PLINE. (DBTDC( 1),DATA( 1),IJ,I,0 0,1. ) 59

Computer Program 2 (Concluded),, R I) I ))R4, PDSHLNI\. ( ) TDC (1), REST ( 1 ), J? I, 0 5, 1. ) P L T F il). l,,l I R lb 0 T F L L F I l WH,' R )( POR4 TELIL. ( RFST ),I F TFL L. (F) ATA) F'Il F' L T r ilXT-S FT T'f POI.1 TT. D j'i F1.r.2,F5.2,F4.2,S51,F6.2, S6,3(FR.'FV,F6. 'FV' )":, 1 RTnDC(P), CivRFF(P), FPRREF(P), 100.'*(1. - ER.F.(.ABS. 2 (R KEF(P) - Ar,(P))/SORT.(2.:- ( RFFFRR ( P ) + A.)JRR ( (P) ) ) )), 3 REF(P)?, S,)RT.(RFFERR(P) ) BL('I(P)t ), ORT. (HLERR(P) ) z AD, ( P ), S(-)RT. (A I),IFRR ( P ) ) F t lN F 'N I 1t\i TELL. (DAT) R GCt, = 1 + I R! N. ( (VALIES(S ) - V AL U ES( 1) )/E L I T) )EL = I RU),,!). ( V AL IFS ( 6 ) /!DEL I lT N I i D AT = 1 + I R 01DUD. (( V A L S (7 ) VA L U fs ( S )5) / E L I NT ) / EL fED = R(N, + I\il v!F)AT':)FL F\/= F\/ + 2 R WT, F\I = FV - 1,R [ )OPRiNT., P'T, JH]1/11H-5(F13. 'F\', 2H @iF ].(0.4,1H,)/(S 1,5(F13.'.F\V',\ H -,)F]0.4 1 H ) )1:- $, 2 (I = R(Nl, IEF, T.F. D, )AT( I), DBT)C( I) ) h, I R PD(l P'l,N H SPEC(1) = C. (SPEC ( )) PIUNCH FIRitNAT.$I4,S2,C4,5HR!\GN F16..10,5H, F{3RF16.1O,7H, END) RF 1.1h.in,5H RTDC:-i'$, SPEC( 1), SPEC(2), DRTDC(BGNI), 2 DRTIC (DEL) - IDRATIC, nBTDC(F IND\) - DEL) PJlI CH. (,PEC( 1 ), SPEC ( 7 ), 7-FV, llV IMIDAT, DEL,)AT( BG, ) ) E'L F ' L F '1\1.F I j > 60

Computer Program 3 Title: Engine Data Reading and Printing Purpose: To read. engine data and. specifications, calculate the mean values and root mean square errors, and. tabulate the experimental observations. Input: A. Engine Specifications and Conditions of Test 1. Runs identification 2. Fuel used. 3. Injector opening pressure 4. Oil used 5. Coolant used. 6. Fuel consumption weight 7. Air flowmeter orifice B. Engine Data 1. Engine speed in rpm 2. Load. in lbs 3. Fuel consumption time in minutes 4. Fuel leakage past injector needle in liters per hour 5. Air pressure before air flowmeter orifice, in psia 6. Air temperature before air flowmeter orifice, in ~F 7. Blowby rate, in ft3/min 8. Barometric pressure, in in. Hg 9. Air surge tank gauge pressure, in. Hg 61

10. Cylinder pressure at the time of I.V. closing above the air surge tank pressure, in psi 11. Cylinder pressure at the point of injection above the cylinder pressure at I.V. closing, in psi 12. Cylinder pressure at the end of ignition delay, I.D.p above the pressure at start of injection, in psi 13. Crank angle at the start of needle lift, in degrees 14. Crank angle at the end. of ignition delay, in degrees 15. Crank angle at the start of illumination, in degrees 16. Inlet air temperature, degrees Fahrenheit 17. Minimum surface temperature of the combustion chamber wall, in millivolts 18. Surface temperature swing due to combustion, in millivolts 19. Exhaust gas temperature, in degrees —Fahrenheit 20. Smoke meter reading, in Hartridge units 21. Oil temperatures at inlet and outlet of the oil cooler, in degrees Fahrenheit 22. Oil flowmeter reading, in cycles per sec 23. Coolant temperature at inlet and outlet from engine, in degree Fahrenheit 24. Pressure drop across the sharp edge orifice of the coolant flowmeter, in in. Hg Procedure: L. Read. and print the engine specifications, conditions of runs, and data, in tabulated form. List of Assisting Programs: L. Program to print a title (TITLE) program 12. 2. Program to calculate the averages and. errors (AVERMS) program 18. 62

NOTE: Items 10, 11, 12, 13, 14, 15, 17, 18 are obtained from the different oscilloscope traces photographed. for the cycle. 63

Computer Piogram 3 Engine Data Reading and Printing (ENGDAT) -NI1GTTT,;, HHAN GE COLMNS MOREl EXTERNAL FUNCTION ENGDAT.(USING,SPEC,ID,DATA) I'R TITLE., LINE, BCDBN., N, SPEC, MAX, USING, USE, USE2, 1 USE3, USE20, END2OO END26, R, S, ID, END, BGN B'N MURE, LACK. LINE = TITLE.(1,SPEC) N = BCDBN. ((SPEC(1I) - SPEC(1') = N MRUKE = N.G. 1 W ' R MORE MAX = N + 2 O'E MAX = 1 E'L USE = USING W'R N.L. 1.OR. MAX.G. USE ERROR RETURN E'L USE2 = USE + USE USE3 = t)SE2 + USE USE20 = 20*USE END20 = USE20 - 1 END26 = 26*USE - 1 R'T $I4,2C1,F5,F4.1,F3.2,F2.2,F3.1,F2,2F2.1,F4.1,F3.1,F4, F3,3 1F4. I, F3, F3. 1, F3. 2, F4iF2-7TI4,F4.. F3. 1,F3, F4.1,2F3.*$, 2 (R = 0, 1, R.E. N, ID(R), ID((ISE+R), ID(USE2+R), 3 (S = R, USE, S.G. END20, DA'TA(S)), -- 4 ID(USE3+R), (S = S, USE, S.G. END26, DATA(S))) T'H CHANGE, FOR R = 0, 1, R.E. -NS = USE3 + R 'R ID(S).NE. ID(R),i T'O NOGOOD S = S + USE2 TORF = DATA(S) W'R.NOT. LACK.(TORF).AND. TORF.L. 40., 1 DATA(S) = 100. + TORF S = S + USE2 PBAR = DATA(S) W'R.NOT. LACK.(PBAR) W'R PRAR.G. 2. PBAR = 20. + PBAR O'E PBAR = 30. + PBAR -E 'L DATA(S) = PBAR W 'R MORE T'H COLMNS, FOR S -= 0, USE, S.G. END26 AVEERR. ('N,DATA(S)') E'L BGNEND.(LINE,6,MAX —,BGN,END,DONE 1 ) W'R END.G. N,. END- = N P'T $10H-DATA SET C4,4H HASI5,12H RUNS. THE C4,9H ENGINE (C4 1,14H- SL-EEVE, IVC @C4,13H DBTDC) USED C4,7H FUEL (C4,7H PSI), 2C4,10H OIL, AND C4,9H COOLANT.*$, SPEC...SPEC(8) '-TT-_- $'114HO FOR USE SPEED LOAD FUEL AIR BLOW ROOM 1-SURGE-@IVC-@INJ-RIS DBTDC AT START OF AIR MILLVOLTS EXHAUS 2T/114H RUN W 0 RPM LBS MIN L/HR PSIG F CFPM INHG I 3NHG PSI PSI PSI LIFT RISE IILLUM F MIN INC F HU/( 4I5,2(S1[C1),F-8,F6.1,F5.2,F4.2,F6.1,F4,F4.1,2F6.1,F5.1,F5,F4,F 57.1,2F6.,F5F5,F5F5.1,F5.2,F5,F3)*$, 6 —T-= BGN, 1, -R.E. END, ID (R), IDJ(SE+R), ID(USE2+R), 64

Computer Program 3 (Concluded) 7 (S = R, USE, S.G. END20, DATA(S))) ' tH11 JR MR I DONEl W'R MORE, P'T $5H MEANF12,F6.1,F5.2,F4.2F6,F6.1,F4,F4.1,2F6.1,F 15.IrF5, F4, F7. 1,2F6. 1, 5, F5.F. 22, F F5, F3/5H ERRSF 12, F6. 1, F5.2, 2F4.2,F6.l,F4,F4.1,2F6.IF5.1, F5,F4,F7.1,2F6.1,F5,F5.1,F5.2,F5 3 F 3-F34-,- TR-( — - IN r R.E MAX, 4 (S = R, USE, S.(. END20, DATA(S))) M[ORE:2 G.INENEb).( L I MiE, 4, MAX, pBGUM END, DNIE2 ) W'R END.G. N, END = N P1- $-3-TR -— FOR CRANKCA-SE OILS COOLANT SYSFEM/38H RUN OUT(F 1)INC CPS OUT(F)INC INHG/(I5,F7.1,F5.1,F4,F7.1,2F5.1)"$, 2 --- ( —1RI- = ISRGN7, -R-E. END), 1D(R), 3 (S = USE20+R, USE, S G. END26, DATA(S))) I 'LI MJRtZ DONE2 W'R MORE, P'T $5H MEANF7.1,F5.1,F4,F7.1,2F5.1/5H ERRSF7.1,F5. lrl,-F4 —,-F71:T5~,- (R =-N, i, R.I. MAX, 2 (S = USE20+R, USE, S.G. END26, DATA(S))) E'N 65

Computer Program 4 Title: Engine Data Calculations Purpose: To calculate the different parameters of interest in the study of the combustion process. Input: Same as ENGDAT (engine testing data and. specifications) see ENGDAT input. Procedure: The following calculations, together with their mean values and root mean square curves are calculated. 1. Brake horsepower 2. Brake mean effective pressure, in psi 3. Brake specific fuel consumption in lb/hp/hr 4. Fuel-air ratio 5. Inlet air/cycle in lbm/cycle 6. Air blowby per cycle in lbm/cycle 7. Residual exhaust gas in lbm/cycle 8. Surge tank pressure in psia 9. Volumetric efficiency in % 10. Temperature at inlet valve close in degrees Farenheit 11. Average index of compression from inlet valve close to beginning of injection 12. Pressure at start of injection, psia 13. Density at start of injection, lbsm/ft3 14. Temperature at start of injection, degrees Rankine 15. Average index of compression during delay 66

16. Average pressure during delay, psia 17. Average density during delay, lbm/ft3 18. Average temperature during delay, degrees Rankine 19. Pressure rise delay in Msecs 20. Illumination delay in Msecs 21. Minimum cylinder wall temperature in degrees Farenheit 22. Maximum temperature swing during combustion in degrees Farenheit 23. Lubricating oil flow rate in gallons/min 24. Rate of heat loss to oil in Btu/sec 25. Percent of heat loss to oil 26. Coolant flow rate in gallons/min 27. Rate of heat loss to coolant in Btu/sec 28. Percent of heat loss to coolant List of Assisting Programs: 1. Program DB4Tll (9) 2. Program CYLVOL, CYLGRA (10) 35 Program BBRAN, BBLFT3, BBFAR (11) 4. Program ENGDAT (3) 5. Program INTDER (7) 6. Program TITLE (12) 7. Program FULHCR, FULDEN, FULFLO (13) 8. Program 14 (coolant and oil properties) 9. Program MEAN (15) 10. Program AIRFLO (17) 67

11. Program AVEERR (18) 12. Program THERMO (19) 13. Program LACK (20) 68

Computer Program 4 Engine Data Calculations (ENGCAL) EXTERNAL UNC I UN ENGCAL. (USING,SPtC, 1V,)A IA,CALC ) D'N STORE(54), (DAT, CAL)(28), (P, D, T)(10) T'R —ENGDAT, LIN? E SPEC, N, MAX, USINGt USE, USE22, END22, 1 END28, E, BCDBN., R, S, I, ID, RUN, END, BGN B' —N MTORE-, LACK., LACK2. LACK3., LACK4. LINE = ENGDAT.(USING,SPEC,ID,DATA) N = SPEC(1) MORE = N.G. 1 W'MR MORE MAX = N - 2 MAX = 1 t' L USE = USING( -— TS-E2 =- 2 ES ------ ---- - _ END22 = USE22 - 1 -.END278 --- —US E ----- V'S DYNAM = 3000., 3571. V'S BMEP = 3.689, 3.18( V'S EFF = 2414.38, 2483.42 R-WT SPET2TP. T __ —_- E - -A_ __-$_ _ _ E = 0 E =1 t'L RATIO = COMRAT.(VCLEAR, SPEC(2), SPEC ( 3)) --—.CUEAR --..VCL`EAR /71728. IVC = BCDBN.(SPEC(4)) i vC' —= --- T ----- _ -VC VIVC = CYLVOL.(IVC) DEN60 = F-ULPRU. (SPEC( ), HTUC,H I VAL) RVAPOR = 1./(17.908 + 1.503*HTOC) K EX — =- 3757 + —4. —7697HTO C OIL ID. (HAVOIL, SPEC(7) ) C.L IcD. ( 0, SPE - )-}T DEN80 = COLDEN.(80.) F-UE L = HEt I VAL/360000. HEAD = 70.3863/DEN80 -.08333333333 — T-rH- CM P_ T uR -O —W --- —, -r, R -- N - S = R ( = -— T-,-'. E. 29t -A-TTT-"= ---- AT S, 1 CAL(I) =- 0., S = S + USE) W' R.NI. LACK. (VCLEAR ) W'R.NOT. LACK.(DAT(1)), CAL(1) = DAT(1)*DAT(2)/DYNAM(E) c APLT2 — =T B-MEP ( EDAT2 -) D- --- E'L — S ---=' —U S R - -R FUEL = FULFLO.(ID(S),DAT(3),DAT(4)) AIR = A IR —LU. ( I ( S+USt J,UDA I(6), VA I(5), DA I(8 ) DA (9)) W'R.NOT. LACK.(FUEL) -C-AL-3-T --- = FU E L/-C A - () - CAL(4) = FUEL/AIR -'L PRAR =.4911570*DAT(8) VINJ = CYLVOL.(DAT(13)) W'R.NOT. LACK2.(PBAR,DAT(9)) CAL(8) = PBAR +.4911570*DAT(9) W'R.NOT. LACK.(DAT(10) ) CAL = CAL(8) + DAT(10y) 69

Computer Program 4 (Continued) W'R.NOT. LACK.(DAT(11)) CAL(12) = CAL + DAT(11) W'R.NOT. LACK2.(VIVC,VINJ), ~1 CAL( 1) = ELO.-C-AL ( 12)/CAL)/ELOG.(VIVC/VINJ) E'L E'L E'L W'R 1WOT LACK.( DAI() ) CYCLES = 30.*DAT(1) ) NAL( 5)- = A IR/CYC L E S RUN = ID(R) rf-R —R[ JN.GE E.A-N-D.R - -. T.R-UN-. 7 AND. LACK.(DAT(21) ) TBLO = DAT(24) TRLO = DAT(21) W'R.NOT. LACK.(DAT(7)), CAL(6) = 16.408644* -- 1 — 'S 'ORT- -(-BBL —FT3 —.(Tr BLO, PBAR,.3B7110 ))*DAT A( 7 )/CYCL ES E'L T.R MT-T. TACK2. ( VC LE AR, CAR L (T8) ) W'R.NOT. LACK.(CAL(5)),_ ' CALA-(g9- = EFFE )*CAL-(5)/BBLFT3.( DAT(16),CAL(8),.371110) W'R.NOT. LACK2.(CAL(4),DAT(19))..REXH T- -T ---T — 1NJ +CA-ET4-)-EX-17T 1. + C AL ( 4 ) ) CAL ( 7 ) = BBLFT3.(DAT( 19)+75.,CAL(8),REXH)*CLEAR '"W'R.N(JI. LACK. (CAL(5)) GAS = CAL(5) + CAL(7) RG —= —TCAL-5 — 37 0 + CAL ( 7) *REXHR) /GAS GAS = 1728.*GAS C A L(") —BFR. —CE, / V I VC, RGA S ) CAL(13) = GAS/VINJ CAL ( 14) = BBRN. (CAL ( 12),CAL ( 13), RGAS) W'R.NOT. LACK3.(DAT(12),DAT(14),CAL(14)) P —= C:n-IT-i - D = CAL(13 ) - -- T -. -C-AL-14) DEL = (DAT(14) - DAT(13))/10. FUELIN = 1728.*FUEL/CYCLES GASR = GAS*RGAS T'H DEL-AY, FOR I = 10, -1, I.E. 0 VAPOR = PART(I)*FUELIN — V'S PART 1) =.025, -.050,.075,.l100.125,.150,.175,.200, 1.225,.250 MIX = GAS + VAPOR RMIX = (GASR + VAPOR*RVAPOR)/MIX V = CYLVOL.(DAT(13) + I*DEL) D(I) = MIX/V W'R I.E. 10 P(10) = CAL(12) + DAT(12) T(10) = BBRA P(10),(D10),RMIX) INDEX ELO (T(10)/T)/ELOG. (VINJ/V) - CAL(15) = 1. + INND -- K = T*VINJ.P.INDEX T(I) = K/V.P.INDEX P( I) = D(I)*RMIX*T( I)*BBCFAC. (D(I),T( I),RMIX) E'L C:A L ( 16-) = MEAN. ( 1,,-STORE ) CAL(17) = MEAN.(11,D,STORE) -CATiL ( 18) = MfEAWF. (T1-i,1,TSTO-RIE ) DELAY 70

Computer Program 41 (Continued) E'L - t'L E'L t'L WIR.NOT. LACK.(DAT(13)) CA = 166.6666667/DAT(1) W'R.NOT. LACK.(DAT(14)), CAL(19) = CA*(DAT(13) - DAT(14)) W'R.NUI. LACK.(UAI(15)-J, CAL(20) = CA*IC AI(13J - DAI(15)) E'L CAL(21) = THERMU.(DAT(17)) W'R.NOT. LACK2.(CAL(21),DAT(18)), 1 CHEM(1)) AL(22) = IHtRMU.(UAI(21)) CAL(23) =.071165*DAT(23) W'R.NJI. LACK3.(UAI(Z1) DAI(Z2),HAVUIL), (CAL(Z4) =.UOZZZ8* 1 O}LDEN.(DAT(21)-DAT(22))*CAL(23)* 2 -- ILCP.(DAI( 2i )-DAI (22)/2.-DA I ( 2Z) W'R.NOT. LACK4.(DEN80,DAT(24),DAT(25),DAT(26)) TCOLIN = DAT(F24) - DAT(25) ROOTH = SRT.(.1666666667 + DAT(26)*HEAD) NUCOL = CULNU.(TCOLIN) CAL(26) = 6.15836*ROOTH*(.5 + 1 SORT.(.25 +.010205*NUCOL/ROOTH)) RN = 4391.75*CAL(26)/NUCOL W'R RN.G. 2000. CAL(27) -=.002228*COLDEN.(TCOLIN)*CAL(26)* 1 - - CULCP. (DA I (24 )-DA( 2 ) /2. ) *DA (25 ) O' E CAL(26) = - -- E'L E' L W'R.NOT. LACK.(FUEL) OFUEL = FUEL Q*FUEL CAL(25) = CAL(24)/OFUEL CAT2WW= CAL(2 )//Q-UEL E'L S = R COMPUT (I = 1, 1, I.E. 29, CALC(S) = CAL(I), S = S + USE) W ' R MURE T'H COLMNS, FOR S = O, USE, S.G. END28 AFEER. ( N, CALC ( S J ) E'L O UL MNS M UK t I bL bl t N U ( L 1 I1 t t M A Xt bLNlN Nt!:N U L UUN tI ) W'R END.G. N, END = N P'T $12H-ENGINE WITHF6.2,12H/I RATIO HASF7.4,27H CUIN CLEARAN 1CE. FUEL WITHF6.3,12H/1 RATIO HASF6.2,29H LBM/CUFT (@60) AND 2 LIBERATESF6,9H BTU/LBM.*$, 3 RATIO, VCLEAR, HTOC, DEN60, HETVAL -P'1T-$-i29HO FOR BRAKE BMEP BSFC-FUEL/ CYCLE(LBM/1OO00) SURGE 1 EFF iIVC AT START OF INJECTION AVERAGED DURING DELAY DELA 2Y(MSECJ) WALL(-)/129H RUN HP PSI #/HRHP AIR AIR BLU 3W EXH PSIA PCT F INDEX PSIA #/CUFT R INDEX PSIA #/CU 4FT R PRISE ILLUM MIN INC/(I5,2F6.1,F6.3,F6.4,3PF7.2,3P2F5 5.2,F5.1,F6.1,F4,2(F7.3,F5tF6.39F5),F7.3,F6.3,F5,F4)*$, 6 (R = BGN, 1, R.E. END, ID(R), 7 (S = R, USE, S.G. END22, CALC(S))) I! U MRE 1 DONE1 W'R MORE, P'T $5H MEAN2F6.1,F6.3,F6.4,3PF7.2,3P2F5.2,F5.1,F6. 11,F4, 2(F7.3,F5,F6.3,F5),F7.3,F6.3,FS,F4/5H ERRS2F6.1, F6.3, F6. 24,3PF7.2,3P2F5.2,F5.1,F6.1,F4,2(F7..3F5,F6.3,F5),F7.3,F6.3,F5 3,F4*$, (R = N, 1, R.E. MAX, 71

Computer Program 4 (Concluded) 4 (S = R, USE, S.G. END22, CALC(S))) MR;Rt BGNEND. ( L I NE, 4, MAX, BGN, END, DONE2) W'R END.G. N, END = N V'S —UT2 =U $37H- FOR CRANKCASE O-LS CMOLANT SYSTEM/5H RUN2 1(16H GPM BTUJ/SEC$, 601260346174K, $I5,F6.2,2F5.1,F6.1,2F5.1* 2$ P'T OUT2, (R = BGN, 1, R.E. END, ID(R), 1 (S = USt22+R, USE, S.G. END28, CALC(S))) T'O MORE2 DOtEqE7- W '-R —:2RE -,-s —' -T- 5i-E A —NF6 -.2,-2-F5;-, —F 6.1,2F5.1/5H ERR SF6.2,2F 5.1 1,F6.1,2F5.1*$, (R = N, 1, R.E. MAX, 2- (-S E —US2 — R, USE S.G. E ND2 8, CAL C(S)) ) F'N LINE t7 1

Computer Program 5 Title: Fuel Injection System Analysis Purpose: To calculate the fuel mass flow rate, the accumulated injection and the average coefficient of discharge over the injection period~ Input: A sequence of needle lift, cylinder pressure, and fuel pressure, over the period of injection (are fed from oscilloscope traces). Procedures: 1o Use ENGDAT to calculate the engine parameters 2o Use program AREAS to calculate the effective area of fuel flow 3~ Calculate theoretical mass flow rate of fuel Q = A \2g(P felcy /P fuel cyl. fuel 4. Calculate the theoretically accumulated. injection over the injection period 5~ Knowing the actual accumulated fuel/cycle from ENGCAL and. the theoretical accumulated fuel/cycle, therefore an average coefficient of discharge is calculated. 6o Calculate the actual mass flow rate over the period of injection 7~ Gives a printed, punched or plotted values of mass flow and. accumulated injection over the injection period 73

Computer Program' 5.iuel.InJeeti:n System Analysis AGAIN D'N SPEC(19), ID(3),,DATA(21), CALC(-20), (DBTDC, NL, FP, CP, -1 SAVE, AREA, LBMHR, DO, D1, D2, D3, D4., LBM)( 1000)?, - 2 STORHE-5000) EOUIVALENCE (SAVE, AREA), (STORE, DO, LBM), (STORE(1000), D1-) 1,( STORE(2000 ), D2), (STORE(3000), D3), (STORE(4000), D4) I 'R -IRO(UND., NIJMDIV, BCDRN., NUMINT, NUMDAT, ENDDAT, NUMSEQf, 1 ' E"NDSEI, I, FV, FVF, J, LII\IE, START, STOP, SPEC F'E FVF ENGCAL. (,SPEC, ID( 1),DA TA( 1) CALC () ) P'T $1H-/1HO*$ AREAS1. DENFUL = FDULEN.(SPEC(4),DATA(9) ) FUEL = FULFLO.(11 (2 ),)ATA(3),DATA(4))/DATA( 1 )/30. R'T $S15, F16.1O, S5 F16. 10,S7 F16.10:'$, BEGIN, EVERY, END ' NUMIN\T = BCDBN.(SPEC(7) ) NUM.DAT = I +-'IROUND.((END - BEGIN)/EVERY) ENDDAT = 1 + NllUM INT ' INUM.DAT NUMlSEO = ENDDAT - NIIMINT,J'R NUMSEO.0. 1000, T'O FIN ENDSEO = NiUtSE~ + 1 DEL S -= EVFRY/i\!N.L, I NT DBTDC = BEGIN — -DElISEO (I = 1, 1, I.E. EN\DSEO, 1 DRTDC(I) = DBTC + I*DOELSEO) READ. (NL,2) READ. (FP,4) READ. (CP,4) LRMHR = SOR T. ( DENFUL ) / 415.53855 LBM = LBMHR/-21600./DATA(1) (I = 1, 1, I.E. ENDSEO, 1 P = FP(I) - CP(I), 2 SAVE(I) = P/SORT. (.ARS.P), 3 LRMHR( I) = AREAS3. ( NL(I ) )SAVE( I )) AREAS2. ( FUEL/MEAN. ( NUIJMviSEO, LBVHR ( 1 ), STORE ( 1 ) ) 1 /(DBTDC(NUi'SEO)-DBTDC ( 1 ) )/LBM ) (I = 1, 1, I.E. EN\IDSEO, 1 AREA = AREAS3.(INLL(I)), 2 LBMHR( ) = AREA*SAVE( I ), 3 AREA(I) = AREA) DB4T11. (NUMSEQ,DELSEO 1, LBMHR( 1 ),DO( 1 ),D1 ( 1 ), D2(1 ), D3( 1 ), 1 04( I)) LRM(1) = -0. (I = 2, 1, I.E. ENDSEO, 1,J = I - 1, 2 LRvBM(I) = LRIvM(J) + INTDER.(DBTDC(J),DBT1DC(I),DBTDC(1), 3 NUMlSEO,DELSEO, 1, LBHR ( ) D1 (1), 4 D2(1),D3(1)D4(1))) COEFF = FUEL/LM (. I\NUMSEO)/L BM P'T $1H-/42HOFUEL DENSITY (@ TEMPERATURE OF COOLANT) =F6.2,43 1H LBI/CUJFT, TOTAL FUEL INJECTED PER CYCLE =6PF7.2,12H LBM/10 200000/1H-/50H-INTEGRATION OF DATA GIVES DISCHARGE COEFFICIENT 3 =F7.4*$, DENFUL, FUEL, COEFF LBMHR = COEFF*LLBMHR 'LBM = C.OEFF'*LB RM FUEL = FUEL/100. (I = 1, 1, 1.E. ENDSEO, 1 L.BMHR(I).= LBMtHR':LBMHR( I), 2 LBNM(I) = LBM*LBM(I)) L NE = 60 74

Computer Program 5 (Concluded) MrRE RGNEND. ( LTNE, 6, NUMDAT, START, STOP, DONE) EN O\DAT = 1 + NU M IN T 'STOP P' T $1H-SS,48HI ----)DATA.FR(OivI SEO)UENTIAL PHOTO' ANALYSIS ----I 1!13( 1H-)30HIlNCLUJDFS DISCHARGF C(U)EFFICIENT.12(1H-) 1HHI/132HO A 2T NEEDLE LIFT FI..EI_ PRESSUIRE CYLINlDER PRESSUPRE EOUIIVALENT 3 ARE. RA-TFE OF Ii\!,JFCTI[OlN, ACCvI.)llJLATED. IN!,.ECTION FRACTION INJ _ 4(ECTTFD/7H D)RT-)C\S6,4HfMILSS1lO,4HPSIAS12,4HP.SIASlO, 131SH IN/1(O00 5000S7,8 HL FIv/HOURS12, 1 HLI.;/l OOO()0OOSl- 14,3.HPCT/(F7. 1, F10.2 F 14,F ~~_ ~ 617. 1 2F.]8.1. 6PF21.2,F2].2)':' 7 ( I = ]. + N \!1i;' I i\lT' ST AR T, n R JlT I Ii! T, I. E. E N D A T P DRTC (I), 1 ( I ), FP ( I ), CP ( I ) AREA (I), LMHR ( I ) LBM (I) 9 LR i( I )/F.FIL ) Tf' M'ORF DO)NE W'R SPEC ( ).. $PN CH$ PI!NCH F!ORMAT I4,6HIi\!NJCTt 5HKGN F16.,1 SH. FOFRF1h. 1O,7H, ENhlD I F1 h6.1.,S5H KTDC".-'.~, 1)(1), D)TDC( 1), IDELSEO(, DBTDC(NITNUMiSEO) PUtINCH. ( ]. ( t $/HR( 3 i!)i"if t i LB i H R ( 1 ) ) PIIN xlC H. ( I 1) (.) 1, ACC S t -3. i\!i..JUl',' S,.1 I M ( 1 F' I T'O AGC, AIN I N REAf). (D)AT, F\/) FVF = 7- F\ R'T $S10),iOF7. 'FVF: ', (I = 1, I\il.JMINtT, I.E. ENI)DAT, DAT(I)) I! T ERP. ( il.J ivi T, D RT C ( I ),!t I J I NU I T,: A T ( 1 ) ) F 'N. FII'I E 'i F I i~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~i~~~~~~~~~~~~~~~~~~~~~ 75

Computer Program 6 Title: Calculation of Equivalent Area of Injection Purpose: To calculate the effective area of injection at any needle lift, where effective area is the area to which we can write AP QI = C A 2g d. eff. p Input: 1. Needle lift 2o An assumed. value of coefficient of discharge Procedure: The pressure differencebetween fuel at inlet to injector and fuel out of the injector is measured. Due to the change in area between inlet and. outlet an effective area was derived. using the energy equation. 76

Computer Program 6 Equivalent Area of Injection as a Function of In.ector-Needle Lift '(AREAS) L'F E'XTERNAI FUNCTION (ARG) D'N DInM(4) P' R PI (3.141592654) E'O AREAS1. R'T $4F10.5,F10O.2,F1.4*",, DII'...DIM(4), COEFF AHrLES = P I:- D I M*. 6 ARODY = PI*DIN' ( )*f)Ift( 1)*.25E6 TAN = (DIMi(2) - DIM(1).)/2./DIM(3) ALPHA = ATAN.(TAN) COSINE = COS. (ALPHA) RETA = DItvi(4)*PP I/360. DIF = RFTA - ALPHA RATIO = SIN.(RETA)/SIN.(DIF) KI. = PI*' (DI FN 1 ()"'IFRATIO 1000 K2 = 2.'4PI'-()T'IF*COSINE*TAN + COS.(BtETA) - COSINE) RAT IO*R TIO P T,132. H —RAT~ OF INJLECTION = OISCHARIGE COEFFI CIENT * EOUI V\/AL lENT AREA * SORT.(FtUFL DENSITY I FIEL PRESSURE - CYLINDER PRE 2SSIJREI ) / 415.53855/14H (LBH/Hl OUR.)S32,13HS0) IN/1000000Sl 11., 31OH(LBil\/CtJFT)S8,6H( PSIA)S12,6H( PSIA)/18HOINJECTOR HAS FOURF7. 45,43H INCH HOLES? COtINTACT SlJRFACE HAS D)IAMETERS F7.5,2H &F7. 55,11H AND HEIGHTF7.5,15H, TIP.IANGLE ISF7.2,RH DEGREES/132HOE 60JIVALENT AREA = ]./SC-)RT.(1/(OITLET AREA FOR NEEDLE & SEAT).P. 72 + 1./(AREA OF HOLES).P.2 - (DISCHARGE COEFFICIENT/AR.EA OF BO 8DY).P:2)/S31,6HMILS" ( SF6. 1,2H -F7.4,6H*MILS)F21.1,F44.1*-'$, 9 DIM...DIM(4), K1, -K2, AHOLES, ABODY T'"O SKIP E'O AREAS2. COEFF = ARG SOQUARE - COEFF/ABODY SOUARE = 1.H ES/OLES/AHOLES - SOUARE*-SOUARE F 'N E'O AREAS3. MILS = ARG W'R MIILS.LE. 0. F 'N 0. O' E AOUT = M IL S * (K + K 2-',M v!ILS) F' N 1. /SORT. (1. /AJT/AOUT + SQCUJARE ) E'L E' N 77

Computer Program 7 Title: Integration of a Given Data Y( ), Taken at Equal Intervals of x Purpose: To apply numerical integration Input: 1. Data to be integrated. 2. Adjusted values of data and. derivatives from applying DB4Tll (curve fitting program) Procedure: The given data are curve fitted with the best 5th degree polynomial for each point, the derivatives are found. and used in expressing the function accord.ing to a Taylor series expansion that help in performing the integration. 78

Computer Program 7 Integration of Given Data (INTDER) L'F EXTERNAL FUNCTION INTDER.(FROM,'TO,BGN.,N,DEL,ADD, DO,D 1D2, D3D,-D4) I'R LOWERI, UPPERI, N, ADD, ADDS, ENDI, I, AT DELX = DEL LOWERZ = (FROM - BGN)/DELX UPPERZ = (TO - rGN)/DELX W'R LOWERZ.G. UPPERZ ANSWER = LOWERZ LOWERZ = UPPERZ UPPER- = ANSWER ANSWER = -1. O'E ANSWER = +1. E'L LOWERI = LUWERZ +. 5 UPPERI = UPPERZ +.5 W'R LOWERI.L. 0 *OR. UPPERI.G. N - 1, ERROR RETURN LOWERZ = LOWERZ - LOWERI UPPERZ = UPPERZ - UPPER I - ADDS = ADD LUWERI = LOWERI*ADDS UJPPERI = UPPERI*ADDS ENDI = UPPERI - ADDS ZERO.(SUMO,SUM2,SUM4) (I = LOWERI + ADDS, ADDS, I.G. ENDIt SUMO = SUMO + DO(I), 1 SUM2 = SUM2 + D2(I), SUM4 = SUM4 + D4(I)) F 'N ANSWER*(ENDS.(.5, LOWERI) - ENDS.(LOWERZ, LOWERI) + DELX* 1 (SUMO + DELX*DELX*(SUM2 + DELX*DELX*SUM4/80.)/24.) + 2 ENDS.(UPPERZ,UPPERI) - ENDS.(-.5,UPPERI)) I'N ENDS.(ZAT) X = Z*DELX I = AT F'N X*(DO(I) + X*(D1(I) + X*(D2(l) + X*( D3(I) + X*D4(I) 1 /5. )/4. )/3. )/2. ) E'N E'N 79

Computer Program 8 Title: Best Straight Line to Fit a Group of Points Purpose: To curve fit the given data Y according to the relation Y = A+Bx and to give A, B, standard error in A, standard error in B, an estimate of standard error in data, standard errors in calculated values, adjusted values of Y, deviations of data from adjusted values and probability of occurrence of deviations. Input: A sequence of Y data points at equally spaced intervals of x. Procedure: A least square best fitting straight line technique is applied to the given data. 8o

Computer Program 8 Best Straight Line to Fit a Group of Points (BLINE) WO (06 JAN 1967 VERSIONJ PROGRAM LISTING...... BLCNE. ) CL3tNE, F L SEE.):L Z.I... bLN.., ) W N.T..NE EXTERNAL FUNCTION (NRESULT,X,Y) INTEGER N, G0OD, LAST, It, TYPE, BAD BOOLEAN NOPTS, SAMEX, NOERRS, LACK. DIMENSION ANSWER(5) ENTRY TO BLINE. GOOD = N LAST = GOOD - 1 ZERO. (SUMX, SUYSUMXXYSUMXY,SUMYYI NOPTS = lB SAMEX = 1B THROUGH SUMS, FOR I = O, I, I.G. LAST XI = X(l) YI = Y(I) WHENEVER LACK.(XI).OR. LACK.(YI) GOOD = GOOD - 1 OTHERWI SE SUMX = SUMX + XI SUMY = SUMY + YI SUMXX = SUMXX + XI*XI SUMXY = SUMXY + X I*Yl SUMYY = SUMYY + YI*YI WHENEVER SAMEX WHENEVER NOPTS NOPTS = OB XFIRST = XI OTHERWISE SAMEX = XI.E. XFIRST END OF CONDITIONAL END OF CONDIT IONAL END OF CONDITIONAL NU4 = GOOD DEL = NUM*SUMXX - SUMX*SUMX WHENEVER DEL.E. O..OR. SAMEX, ERROR RETURN ANSWER(1) = (SUMY*SUMXX - SUMX*SUMXY)/OEL ANSWER(l) = 0. + ANSWER(l) ANSWER(3) = (NUM*SUMXY - SUMX*SUMY)/DEL ANSWER(.3) = 0. + ANSWER(3) NOERRS = GOOD.E. 2 WHENEVER NOERRS OBS = -0. OTHER WI SE OBS = (SUMYY (SUMY*SUMY + ANSWER(3)*ANSWER(3)*DEL) [1 /N!UMN)/(NUM - 2.) OBS. -= O. + C.BS END OF CONDITIONAL CAL = OBS/NUM AVE = SUMX/NUM MU = DEL/(NUM*NUM) ANSWER(O) = SQRT.(2.*CAL) ANSWER(2) = SQRT.(CAL*(I.. + AVE*AVE/MU)) ANSWER(4) = SQRT,(CAL/MU) ANSWER(5) = SQRT.(OJBS) MOViE.... ANSWER(S t,RESULT.RESULT(5)) SUMS 81

Computer Program 8 (Continued)' F. UNCI. TON RETURN __ VECTOR VALUES, FUNCT(l)} = OB 0,Bt 08 08t 08..... E:NITRY.... TO CL. N E.... TYPE = I.TRANSFER _TO..BEG _ N ENTRY TO ELINEo TYPE....2.... TRANSFER TO BEGIN..Y......NTR... D NL. I NE............ TYPE = 3 TRANSFER TO BEGIN ENTAY TO OLINE. TYPE=. 4.. _.... TRANSFER TO BEGIN....ENTRY_....I Q.. kLI.NE.... -.. ___ TYPE = 5 NOPTS =B _ BEGIN FUNCT(TYPE) = 18......... LAST = N- 1 WHENEVER.NOT. (FUNCT(1).OR. FUNCT(3)).AND. NOERRS __. HENEVER FUNCT (5.... _ NONAX YDEV = -0. CALC = -0. BAD = -O TRANSFER TO END5 OTHERWISE SPRAY.. t-Q..,RE SULT. R ES UL.LA..... TRANSFER TO END END OF CONDITIONAL END OF CONDITIONAL THROUGH ALLPTS, FOR I = O, 1 1.*G. LAST XI =-X(I).WHENEVER LACK( X I XI. CALC = -0. OTHERWI SE.......... YCAL = ANSWER(1) + ANSWER(3)*XI YCAL.= 0. + YCAL WHENEVER FUNCT 1) CALC_-.... YCAL.... OTHER I SE WHENEVER.NOT. FUNCT(3).... ERR = XI - AVE ERR = CAL.*.(....+ ERR*ERR/MU);. END OF CONDITIONAL -.... WHENEVER FUNCT( 21........ CALC = SQRT.(ERR) CALC. = 0_.+ CALC.: _...... _ OTHER WI SE WHENEVER LACK.YI )....... C:.AL._.O _.. __...... __ OTHERWISE.....YDE_Y. YE_ _..YL.___.Y CAL _ __ YDEV = 0. + YDEV..HENEVER F.. UNCTi3. _........_.... CALC = YDEV..TiE.IW. - SE.. DEV = YDEV*YDEV/(OBS + ERR)..IHENEVE R.FU.NCT4)............. CALC = 100.*(1. - ERF.ISQRT. (DEV/2.)) 82

Computer Program 8 (Concluded) OTHERWISE WHENEVER NOPTS NOPTS = 08 OTHERWISE WHENEVER DEV.L. MAXDEV, TRANSFER TO ALLPTS END OF CONDITIONAL MAXOEV = DEV BAD = I TRANSFER TO ALLPTS END OF CONDITIONAL END OF CONDITIONAL END OF CONDITIONAL END OF CONDITIONAL END OF CONDITIONAL END OF CONDITIONAL RESULT( } = CALC ALLPT S CONTINUE WHENEVER FUNCT(5) WHENEVER NOPTS, TRANSFER TO NOMAX YDEV = Y(BAD) - ANSWER(1) - ANSWER(3)I;'t,.t!AD)} YDEV = O. + YDEV CALC = 100.*(1. - ERF.(SQRT. (MAXDEV/2.))') Y(BAD) = -0. END5 FUNCT(5) = OB RESULT1O) = YDEV RESULT(1) = CALC FUNCTION RETURN BAD OTHERWI SE END. FUNCT(TYPE) = 08 FUNCTION RETURN END OF CONDITIONAL END OF FUNCTION 83

Computer Program 9 Title: Curve Fitting (DB4Tll) Purpose: To reduce the effect of random errors in data. Input: Data points at equal intervals Procedure: 1. Read. data 2. Statistically adjust the data to fit a 4th degree polynomial through 11 consecutive points by the use of Taylor's expansion up to the 5th term. 3. Give adjusted values of the middle point and the derivatives up to the 4th derivative. These derivatives are used. for another program for integration.

Computer Program 9 Curve Fitting (DB4T11) L'F EXTERNAL FUN\CTION DB4T11. (N,DLEL,ADD,DATA,DO,Dl,D2,D3,[4) I ' R N, NUM, ADD, ADDS (5 ), I, J, 1 STCrP, P D'N (r)ELX,FACTr)R,C)(4), (SUM,DI F)(5), K(6) P ' REGIN N11 1 M = N W'R \,!.)M.L..11, ERRnR RETUtRN REG.IN = 1R V'S DELX = 1. \I'S FACT(3R = 1. a)DDS(1) = AnO, = 0 CON SlTS DELX(I) = I FL':Fi X(.I) FACTOR(I) = I"'FACTOR( J)/EFLX(1) J = I I = I + 1 AinnDS(I) = AOnS(J) + AOnS(l) ^1' R I.L 5, T'O COINSTS STO)P - ( \I.lv' - 6)*ADDS( 1) T,, I.',PT.S, FOR P = AOl)s(5) ADD S(l), P.G. STOP FIRS = iPATA ( P) (I = 1, 1., 1.. 5, SUii = D)ATA(P + ADDS(I)), DIF = - DATA(P - AO)iS(I.)), SUNM(I) = SUM, + DIF, DIF(I) = SUlM - DIF) C (4) (6.-(Stli,(5) - Stlv,(4) - SUCJ(3) + ORS) - SUjIv(2)' + l 4. -:SJM ( 1 ) )/3432. n4(P) = FAC'TOR(4) C(4. ) C(3) = (30. O:D(5) -6.DIF(4) -.22.-,f-I F(3) - 23. *DIF(2) - 1.. 4: I F ( 1. ) )/5148. n3(p) = FACTOR(3)*C(3) C2 ( 2 ) = (15.*S ( 5 ) + 6. ( SM(i4) - SlM ( ) ) - SlM(3) - (19,, SJ!vi] S ) / - 2 5. 0.':CS ( 4)!7(P) = FACTOR(?):-C(2) C(1) = (5.*- DI(5) + 4.. F::) () + 3. ':DIF(3) + 2.*)I F(2) + 1 r-IF(1))/11n. - 17.R*,C(3) Dl(P) = FACTOR(I)-''C,(1) C(0() = (SINI ((5) + StliJU(44) + StliN(3) + SlIU.J((2) + SItJ!((1) + I1 O,0S)/il. - 10.-:,C(2) - 178.'C(4) nn(p) C,(O) ___ 'R BFEGI N', T 'O),FNDPTS IN PTS C ' F p = STOP FNDPTS K(n) = FACTOR(4)C(4) K(I) = 2.'C(2) K(2) = 3.'C(3) K(3) = 4.-:C(4)- _ K(4) = 6.':C(3) K(5) = 12. 'C(4) K(6) = 24.*C (4) T'H SERIES, FOR I = 1, ]., I.G. 5 1' R REGIN O'E,. = P + ADOS(I) E'L 04 (J) - K ( ) D3(J) = (K(4) + Z-'-K(6)) /OFLX( 3) n2(J) = (K(1) + Z':(K(4).+ Z':-K (5)))/DELX (2 1(J) = (C(1) + Z'- ( K( 1) + Z:- (K(2) + Z::K( 3))))/DELX(1) SER TIES nO(J) =C() + Z:(C() + Z'-:-(C(2) + Z '(C(3) + Z':C(4))')).'R P. R E G I NRFGIIN = OR ''0 INPTS F'L F 'N F- 'N\l 85

Computer Program 10 Title: Cylinder Volume and Gradient Purpose: To calculate the cylinder volume and cylinder volume gradient at any crank angle. Input: Crank angle to give corresponding cylinder volume and cylinder gradient. Procedure: A mathematical formula was derived including the effect of a slight wrist pin offset (center line of the wrist pin is offset from center line of the cylinder). List of Assisting Program 1. Program to check for missing data (LACK) 86

Computer Program 10 Cylinder Volume and Gradient (CYLVOL, CYLGRA) EXTERNAL FUNCTION (ARG1,tENGINESLEEVE) I'R ENGINEL, S, SLEEVE B'N HAVEID, VOLUME, LACK. V'S VCLEAR = 4.5610,- 5.377 -0. V'S RATIO = 16.69197512, 13.94055545 -0. V'5 DtL =.0053333335856, 0. V'S A =.25,.257292401 V S 0R = 00666666666667 O. V'S K1 = 183.4819679, 175.3861518 — VS K2 = 35.78470367, 34.79068412 V'S K3 = 143.1388147, 135.2184669 V'S K4 =.624560900,.60(211986 E'O COMRAT. W -R —E\INTNE.E. $ATAC$ S = 0 CO' R-ENGINE.E. $LISI$.AND. SLEEVE.E. $NU.1$ S = 1 S = 2 E'L HAVEID = S.NE. 2 ARG1 = VCLEAR(S) F'N RATIO(S) ' 0 C YLGRA. VOLUME = OB -E CYLVUOL ALPHA = ARGi W'R HAVEID AN. NUI.. LACK. (ALPHA) ALPHA =.01745329252*ALPHA - DEL(S) SALPHA = SIN. (ALPHA). CALPHA = COS.(ALPHA) SBETA = A(S)*SALPHA + B(S) CBETA = SORT.(1. - SBETA*SBETA) W 'R VOLUME ANSWER = KI(S)) - K2(S)*CALPHA - K3(S)*CBETA OC'E ANSWER = - K4(S)*(SALPHA +- CALPHA*SBETA/CBETA) E'L O'E ANSW:ER = - O. E'L VULUMt = 1B F ' N ANSWER E-' N 87

Computer Program 11 Title: Cylinder Gas Properties Purpose: To calculate the compressibility factor, temperature, and. density of the gas, using the Beatti-Bridgeman equation of state. Input: 1. Cylinder gas pressure and. density, in order to calculate the average gas temperature. 2. Culinder gas pressure and temperature, in order to calculate the gas density. Procedure: 1. To estimate the gas temperature at any crank angle, from the measured pressure, mass and cylinder volume, by-u-sing the perfect gas law. 2. To use the above estimated. temperature to calculate the factor as obtained from the "Beatti-Bridgeman Equation" P pRT(l-c)(l+Bp)-Ap2 where: P = absolute cylinder pressure in psia p = mass density in lbsm/ft3 R = gas constant compressibility T = gas temperature in degrees Rankine c = Cp/T3 B= B (l-bp) A = Ao(1-ap) The constants for dry air are obtained from "Fundamentals of Classical Thermodynamics" by G. J. Van Wylen, and Richard E. Sonntag, John Wiley and Sons, Inc. New York, 1964, and converted to the British system as follows: 88

c = 14.0 x 104 B = 0.02550 b = -0.0006089 A = 5e8483 0 a = 0.01068 R* for shop air = 0.371110 psi/(lbm/ft3)~R The value of Z from the above equation is as follows: z = (1 - '')(1+(Bo-B bp)p)-(Ao-A ap) Po o3 o o 0 0 RT 3. To use the above calculated compressibility factor to check temperature calculated. in step 1. 40 To iterate the above steps until the final gas temperature calculated fulfills the Beatti-Bridgeman equation List of Assisting Programs: 1. Program to check for missing data (LACK) *The shop air is supplied, at 98 psig and. 80~F and assumed, saturated. with water pressure of 0o5 psi, i.e. water mole fraction of 0.004454. The correction due to water vapor is 0.2% 89

Computer Program 11 Cylinder Gas Properties (BBCFAC, BBRAN, BBFAR, BBLFT3) L IF EXTERNAL FUNCTION (ARG1,ARG2,RGAS) -- L'ACK —.ACK3-., FAREN E'O BRCFAC. =n ARG1 T = ARG2 R = RGAS W'R LACK3.(D,T,R), T'O NOGOOD ANSWER = Z T ' n —R T1 R N! E'O BBLFT3. T = ARG1 P = ARG2 — R AS- '..._W'R LACK3.(T,P,R), T'O NOGOOD — T — + 59 9 - ------- 9 --- DIDEAL = P/R/T D = DIDEAL COMFAC...-..TE-XT- ZLAST = -Z -. ---..- -.. —. ---..... --- —. --- —- -—.. D = DIDEAL/ZLAST COMFAC. W'R.ARS.(Z - ZLAST).G. 2E-8, T'O DNEXT ANSWER = D T 'O RETURN E'- RBBRAN. —. - FAREN = OR T'O SKIP E'O BRRFAR. FAREN = 1B SKIP P = ARG1 D = ARG2? R = RGAS W'R LACK3. P,,R), T RO ---O, — TO O TIDEAL = P/D/R T = TIDEAL COMFAC. TNEXT ZLAST = Z T = TIDEAL/ZLAST C1MFAC -- _ W'R,ABS.(Z - ZLAST).G. 2E-8, T'O TNEXT W'R FAREN, T = I - 459.69 ANSWER = T T RETURN - - NOGOOD ANSWER =- 0. R E T UR N- - -F' — _N_- -R I'N COMFAC. Z = (1. - 14.0E4*-D/T/T/T)"-(1. + (.02550 +.00001553*,D),-D) - 1 (5.8483 -.06245, D) 'D/R/T F'N F 'N -F'-W 90

Computer Program 12 Title: Title Printing (TITLE) Purpose: To print a-title and. read. specifications to be used. by other programs. Input: 1. Required title 20 Specifications Procedure: The title and specifications are read. according to a certain format the- title is printed, according to another format. 91

Computer 'Program 12 Title Printing (TITLE) MAU 1l MAY 1967 VERSION) PROGRAM LISTING...... T =tr L.. EXTERNAL FUNCTION TITLE.(J0B,SPEC)...._I IMENJS I.OQN 1 D( 31__ REMA.R.... _ __.__RK ( [_...........-... BOOLEAN START, JOB, SPEC NORMAL MODE IS INTEGER WHENEVER START START = OB VECTOR VALUES ID = 1.I.DI_ 1__ 5S8 __. 1 ) TODAY.( ID(2), ID( 3 ) ) IO(2) = ID(2).LS. 18.V. 10(2).RS. 24.V. $000 00$ __. OR WHENEVER JOB 10 = ID0 + 1 END OF CONDITIONAL _ PRINT _FORMAT _SHl/IH-.S16t.98HDIESEL ENGINE IGNITION AND COMBUSTION: JA 1 Y A. BOLT, N. A. HENEIN: COMPUTER PROGRAM BY A. SNIVELY/88H 2 ARMY CONTRACT NO. DA-20-018-AMC-1669T: ORA PROJECT 06720: C 3 OMPUTER PROJECT NO. S986F:13,8H OF JOB C6,15H: COMPUTED ON C 4 6tlH,C5*S ID...ID(3) _ LINE = 8 __..W.HENEVER SPEC __ ___. READ FORMAT $19C4,C3, I1*$S SPEC...SPEC(19), MORE AGAIN WHENEVER MORE.G. 0 READ FORMAT $I1,19C4,C3*$, SPACE, -REMARK...REMARK(19) HEAD = CARCON(SPACE) VECTOR VALUES CARCON = $1H+$, S1H $, S1HOS, $S1H-$, $1H-/1H$._ VEC.,TOR_.ALUES HEAPD(II.).. = $_..._S 26tl9C4,C3*$ PRINT FORMAT HEAD, REMARK...REMARK(19) LINE = LINE + SPACE MORE = MORE - 1 TRANSFER TO AGAIN END OF CONDITIONAL END. F C...JND T INAL____._ _.__ _ _-._.... FUNCTION RETURN LINE END OF FUNCTION 92

Computer Program 13 Title: Fuel Properties FULPRO FULDEN FULFLO (FUEL, HTOC, HETVAL) (FUEL, FAREN) (WEIGHT, MINUTS, LEAK) Purpose: FULPRO, FULDEN, FULFLO, to compute fuel to compute fuel to compute rate properties density of fuel flow Usage: A call on FULPRO, or FULDEN, must come first Arguments: FUEL = fuel identification (4 letter BCD HTDC = H/C atom ratio HETVAL = heating value in Btu/lbm FULPRO = fuel density at 60 F in lbm/ft3 FAREN = fuel temperature in ~F FULDEN = fuel density in lbm/ft3 WEIGHT = timer weight identification ( 1 MINUTS = fuel consumption time in min LEAK = fuel leakage in liters/hr FULFLO = rate of fuel flow in lbm/hr ) letter BCD) Formulas: p60~ = 8824.90/(API + 131.5), p = p60~F-Ax(t-60) flow = LBM x 60/MINUTS -.03531542 x LEAK x p80~F Constants: FUEL $SHoP$ $NO.2$ $MILG$ $CT13$ $CTl9$ HTOC 1.837 1 827 2.141 1.992 1o 999 HETVAL 18370 18500 18905 18705 18700 API 34.79 39. 51 60.89 49.37 49.2 A.023 5.0239.0247.0252.0252 WEIGHT $A$ $B$ $C$ $D$ $F$ LBM.06262.12667.25247 ~ 5007.9985.006262 93

Computer Program 13 Fuel Properties (FULHCR, FULTDEN, FULFLO) MAD (17 MAY 1967 VERSION) PROGRAM LISTING.................... FUL.G.. / FUL. D.t F"L IC.LO EXTERNAL FUNCTION(IDtVALUEl1VALUE2) INTEGER S, ID 10 BOOLEAN LACK., LACK2., NOFUEL VECTOR VALUES FUEL = $SHOP$, $NO.2$, $MILG$, $CT13$, SCT19$ VECTOR VALUES API = 34.79, 39.51, 60.89, 49.37, 49.2 VECTOR VALUES T50 = 374., 516., 220., 370., 342. VECTOR VALUES DEL =.0235,.0239,.0247,.0252,.0252 VECTOR VALUES LBM = 3.7572, 7.6002, 15.1482, 30.042, 59.910,.37572 ENTRY TO FULHCR. FINDS FUNCTION RETURN (1.5*API(S}) - T50(S)/20. + 47.).P..33333333333/2.3498 ENTRY TO FULDEN. FINDS. WHENEVER LACK.(VALUE1), TRANSFER TO ERRORS FUNCTION RETURN DEN60 - OEL(S)*iVALUE1 - 60-.)' ENTRY TO FULFLO. WHENEVER LACK2.(VALUE1,VALUE2).OR. NOFUEL, TRANSFER TO ERRORS S = ID.RS. 30 - 17 WHENEVER S.G. - 1.AND. S.L. 6 ANSWER - LBMIS)/VALUEL - VALUE2*DEN80 OTHERWIISE ANSWER = - 0. END OF CONDITIONAL FUNCTION RETURN ANSWER INTERNAL FUNCTION FINDS. NOFUEL = OB THROUGH FUELS, FOR S = 0 1, NOFUEL- OR. ID.E. FUEL(S) NOFUEL = S.G. 4 WHENEVER NOFUEL, TRANSFER TO ERRORS DEN60 = 8824.90/(API (S) + 131.5) DEN80 =.03531542*(DEN60 - 20.*DEL( S ) FUNCTION RETURN END OF FUNCTION END OF FUNCTION ERRORS FUELS 94

Computer Program 14 Title: Coolant and Oil Properties COLID (FAREN, ID) COLNU (FAREN) COLCP (FAREN) COLDEN (FAREN) OILID (FAREN, ID) OILCP (FAREN) OILDEN (FAREN) Purpose: COLID, OILID to find. identification of coolent and oil respectively COLNU, to find coolant kinematic viscosity COLCP, OILCP to find. specific heat for coolant and oil respectively COLDEN, OILDEN to find density of coolant and oil respectively. Usage: A call on COLID must come before a call on COLNU or COLCP or COLDEN. A call on OILID must come before a call on OILCP or OILDEN Arguments: FAREN = temperature in ~F $EGLY$ for ethelene glycol ID = identification of coolant or oil. $EGLY$ for ethelene glycol $MDV3$ for present oil DELVAC 1330 COLNU = coolant kinematic viscosity in centistokes COLCP = coolant specific heat in Btu/lbm COLDEN = coolant density in lbm/ft3 OILCP = oil specific heat in Btu/lbm OILDEN = oil density in lbm/ft3 ARG1 = 1 if proper identification was used, = -0, if wrong identification, to be used. by LACK. Formulas: For kinematic viscosity v, lnln(v+.6) = Aln(FAREN+459.69)+B For specific heat CP, CP = C+D*FAREN For density p, p = E+F*FAREN 95

Constants: ID A B C D E F $EGLY$ $MDV3$ -4.782178 31. 144543.518953 --- ---. 540.0006237276 72.546342.000 56.694196 -.0253698 -.0200661 96

Computer Program I4 Coolant and Oil Properties (COLID, OILID, COLDEN, OILDEN, COLCP, OILCP, COLNU) MAD (17 MAY 1967 VERSICON) PROGRAM LISTING........ C0OO1-ATr AN. OIL u 7. t? RT'l~$ s EXTERNAl. FUJNCTION(ARG1, ID) I NT EGER ID, COL O IL S B3OOLEAN HAV.COL, HAVOIL, COOLER, NlU, CP, LACK. VFCTOR VALUES A = -4.7.82178' 31.144543,.518933,.54,.0006237276b,.o, 72.546342', 56.694196, -.0253698, -.0200661 VECTOR VALUES HAVCOL = 0B VECTOR VALUES HAVOIL = OB ENTRY TO COLID. WHtENEVFR ID.E. $EGLY$ COL =.0 OTHERWISE COL = 1 END fF CONDITIONAL HAVCCL - rCOL.NE. 1 FUNCT ION RE TURN ENTRY 'T ) OI LID. WHENEVER ID.E. $MDV3$ OIL = 1 ARGI 1. OTHER I SE OIL = 2 AP 1 = -0. END nF CONDITIONAL HAVOIL = OIL.NE. 2 FIJNCT IDN RETURN ENTRY TO COLNU. COOLER = lB NOJ = B. TRANSFER TO BEGIN2 ENTRY Tn CnLCP. COOLER = B1 TRANSFER Tn SPtHEAT ENTRY TO OILCP. COOLER = B03 CP = 1B TRANSFER TO BEGINI ENTRY TO COLDEN. COOLER = LB TRANSFER TO DENSTY ENTRY TO OILDEN. COOLER = OB CP = OB NU = OB T = ARG1 WHENEVER (COOLER.AND. HAVCCL.OR..NOT. COOLER.AND. HAVOIL).. AAND..NOT. LACK. ( T ) WHENEVER COOLER S =- COL OTHERWISE S = OIL END OF; CONDITIONAL WHENE VER NUJ ANSWER = EXP. (EXP. (A(S)*ELOG.(T + 459.69) -+ A(S+I) ) ) -. TRANSFER TO END OR' WHENFVER CP S = S + 2 OTHERWISE S = S + 6 END nF CONDITIONAL ANSWER = A(S) + A{(S+2)*T OTHER W I SE ANSWER = -0. END OF CONDITWItNAL FUNCTION RETURN ANSWER. END -OF FUNCTION 97 SPHEAT DEN STY BEGI N1 BEG IN 2 END

Computer Program 15 Title: Integral Mean Value of Given Data MEAN (N, VALUES, STORE) Purpose: To calculate the integral mean of a sequence Arguments: N = no of values (integer) VALUES = sequence of values STORE = region to store DO, D1, D2, D3, D4 MEAN = integral mean 98

Computer Program 15 -Calculation of the Integral Mean Value of Given Data (MEAN) MAD (17 MAY 1967 VERSION) PROGRAM LISTING.. EXTERNAL FUNCTION MEAN.(NVALUES,STORE )NORMAL MODE IS INTEGER FLOATING POINT INTDER., TO NUMBER = N BGN2 = NUMBER + NUMBER --- BGN3 = BGN2 + NUMBER BGN4 = BGN3 + NUMBER DB4Ti1.(NUMBER, 1., 1, VALUES,STORE, STORE(NUMBER),STORE(BGN2, [ STOREIBGN3),STORE IABGN4) ) TO = NUMBER - 1....-F-'FUNCT I 'N" RETURN INT DER. ( O., TO, O., NUMBER'j,. 1, VAL-UES, S-SO-RE —O BNUM'ER )Y 1 STORE ( BGN2),STORE (BGN3 ).TORE ( BGN4))/ }_TO END OF FUNCTIN 99

Computer Program 16 Title: Interpolating Program and Successive use of DB4T11 for Curve Fitting (INTERP), (USEDB4) Purpose: 1. INTERP to give an interpolated value between data points 2. USEDB4 to use DB4Tll as many times as needed Procedure: A library subroutine is used for interpolating and. an itterative use of DB4T11 is used for USEDB4. 100

Computer Program 16 Interpolation (INTERP) MAD (06 JAN 19'67 VERSION) PROGRAM LI STING......... EXTERNAL FUNCTION (N,XADD1,ATA,BESTNUMDB4) INTFGFR NUIMOnR4 N. mIMn)AT, AnD, NIUMINT, l, NII-RER. STrnPAT ENTRY TO USEDB4. WHENEVER NUJE4. O __ __ _.___ NUMDAT = N D L. = X................ _. ___ ___ _ NUMINT = -ADD R4 T11. INIJMn TF I, tM MINT DAT AREST BEST.REST REST. REST I THROUGH MOROB4, FCR I = 2, 1, I.G. NUMDB4 MOR D004 BD4 %1%LNIJMDAI.2_DEL K.NU-.N., B EST, BESI_.BEST..SESIBES TL:EST S FUNCTION RETURN T- HERLS __ ___ ERROR RETURN FND I'F COND IT INAI ENTRY TO INTERP. NUM I NIT =. __ _.....__ _... _ WHENEVER NUMINT.G. 1 NUMDAT = N_ NUMBER- = (NUMOAT - 1*NUMINT THRnIlUGH IISFTAR, FR E I = I, -.I, I -G- NIIMRFR STOPAT = I +.UMI1NT - 2' THROUGH IISFTAR, FOR I- _'. __-G.___PAT _ USETAB DATA(I) = TAB.(Xt I),X,DATANUMINT,NUMINT,5,NUMDAT,1.) - END OFF CNDITIONAL __.... FUNCTION RETURN FND nF FJNCTI ON 101

Computer Program 17 Title: Air Flow Rate AIRFLO (ORF, TORF, PORF, PBAR, PINLET) Purpose: To calculate rate of air flow Arguments: ORF = identification of orifice combination (1 letter BCD) TORF = upstream temperature (before orifice) in ~F PROF = upstream pressure (before orifice) in psig PBAR = barometric pressure in in. Hg PINLET = pressure after orifice in in. Hg gauge AIRFLO = air flow in lbm/hr Formula: (upstream pressure in psia - DEL) air flow = B t \upstream temperature in ~R Constants: ORF $1$ $2$ $3$ $4$ $5$ $6$ $75 $8$ $9$ $A$ $B$ $C$ $D$ $E$ $F$ $G$ $H$ $I$ $J$ 34 k - #5 and,,#1 #5 and #2 - #5 and #53 -#5 and #4 - 3/32 1/8 3/16 7/32 -D and A D and B -D and C - D and. C and. A -D and. C and B D and C and B and A B 4.214 8.255 17.063 32. 642 67.45 71.67 75.71 84.52 100.10 12.766 23.229 51.74 68.35 81.11 91.58 120.08 132.85 143.31 156.08 DEL 1.20 0 0 0 0.070 0 0 0 1.72 1.61.96 0.270.409.413.54.61.70 102

Computer Program 17 Air Flow Rate (AIRFLO) MAD (17 MAY 1967 VERSION) PROGRAM LISTING....... ANVsF LO. EXTERNAL FUNCTION AIRFLC.(CRF,TORF,PORF,PBAR,PINLET). INTEGER ORF, S BOOLEAN LACK4., LAST ATAC VECTOR VALUES B = 4.214, 8.255, 17.063, 32.642, 6 1 75.71, 84.52, 100.,1( 12.766, 23.229, 51 2 68.35, 81.11, 91.5e, 120.08, 132.85, 143 3 156.08 VECTOR VALUES DEL = 1.2C, 0., 0, 0., 0.,.070, 1 1.72, 1.61,.96, 0.,.270,.409,.413 2.61,.70 7.45,.74,.31, 71.67, 0., I 0.t.,,.54, P = PORF BAR = PBAR WHENEVER LACK4.(TORF,P,BARPINLET), TRANSFER TO ERRORS P = P +.4911570*BAR WHENEVER P.L..930*(PINLET + eAR), TRANSFER TO ERRORS S = ORF.RS. 30 - 1 LAST = S.E. 32 ATAC = LAST.OR. S.G. 15.AND. S.L. 25 WHENEVER ATAC WHENEVER LAST S = 18 OTHERWISE S = S- 7 END OF CONDITIONAL END CF CONDITIONAL WHENEVER S.G. - 1.AND. S.1. 9.OR'. ATAC FLOW = B(S)*(P - DEL(S))/SCRT.(TORF + 459.69) OTHERWISE FLOW = -0. END OF CONDITIONAL FUNCTION RETURN FLGW END OF FUNCTION ERRORS 103

Computer Program 18 Title: Average Values and. Errors AVE (N, VALUES) RMS (N, VALUES) AVEERR (N, VALUES) Purpose: AVE,to find. the arithmetic average of a sequence RMS, to find. the RMS average of a sequence AVEERR, to find. the standard deviation of a sequence Arguments: N = number of values (INTEGER) VALUES = sequence of values AVE = arithmetic average of the nonlacking RMS = square root of the mean of squares of the nonlacking standard deviation of the nonlacking AVEERR = VALUES (N) = AVE VALUES (N+l) = AVEERR 10o4

Computer Program 18 Average Values and Errors (AVEERR) MADl(17 MAY 1967 VERSION) PROGRAM LISTING... brs,, tH Z. AVEE rI. EXTERNAL FUNCTION (N,VALUES) INTEGER Nt LAST, GOOD, S BOOLEAN RMSERR, SQUARE, LACK. OKAY VECTOR VALUES RMSERR = 08 ENTRY TO AVEERR. RMSERR = 18 TRANSFER TO SKIPI ENTRY TO RMS. SQUARE = 1B TRANSFER TO SKIP2 ENTRY TO AVE. SKIPI SQUARE = 08 SKIP2 LAST = N BEGIN GOOD = LAST ANS = - O. THROUGH SUM, FOR S = 3, 1, S.E. LAST VAL = VALUES(S) WHENEVER LACK. (VAL) GOOD = GOOD - 1 OTHERWI SE WHENEVER SQUAREt VAL. = VAL*VAL ANS = ANS + VAL SUM END OF COND ITIONAL OKAY = GOOD.G. 0 WHENEVER OKAY ANS = ANS/GOOD WHENEVER SQUARE, ANS = SCRT.(ANS) ANS = 0. + ANS END OF CONDITIONAL WHENEVER RMSERR WHENEVER.NGT. SQUARE VALUES(LAST) = ANS WHENEVER.NOT. OKAY, TRANSFER TO ERRCRS MEAN = ANS SQUARE = 18 TRANSFER TO BEGIN OTHER WI SE ANS = SQRT.(.ABS. ((ANS - MEANI)*(ANS + MEAN) ) ) ERRORS VALUES( LAST +1 ) = ANS RMSERR = OB END OF CONDITIONAL END OF CONDITIONAL FUNCTION RETURN ANS END OF FUNCTION 105

Computer Program 19 Title: Cylinder Wall Temperature from Millivolt Readings THERMO (MVOLTS) Purpose: To find the Farenheit temperature corresponding to a millivolt reading of an iron-constantan thermocouple with reference at 320F. Arguments: MVOLTS = millivolt difference from reference THERMO = temperature in ~F Formula: DB4Tll, was used. on data from the West Instrument Corporation to find. the following formula (good. within ~.1~F in the range from 32~F to 1015~F) oF = 528.7948 + 324.3723 x (Av) + 2.1981 x (Av)2 + 1.4488 x (Av)3 - 2.0224 x (Av)4 where Av =(millivolt - 15)/10. 106

Computer Program 19 Cylinder Wall Temperature from Millivolt Readings (THERMO) MAD (11 MAY 1967 VERSION) PROGRAM LISTING.......0. TH tM o, EXTERNAL FUNCTION THERMO.(MVOLTS) BOOLEAN LACK. MV = MVOLTS WHENEVER LACK.( MV) FAREN = - 0. OTHERWI SE MV = (MV - 15.)/10. FAREN = 528*7948 + MV*(324,3723 + MV*(2.1981 + MV* (1.4488 - MV*2.0224))) END OF CONDITIONAL FUNCT ON RETURN FAREN END OF FUNCTION 107

Computer Program 20 Title: Check on Missing Data LACK (VALUEl) LACK2(VALUE1, VALUE2) LACK3 (VALUE1, VALUE2, VALUE3) LACK4 (VALUEl, VALUE2S, VALUE3, VALUE4) LACK5 (VALUE1, VALUE2, VALUE3, VALUE4, VALUE5) Purpose: To test for lacking values (i.e., a value of -0). Action: = 1B if any arguments are lacking = OB otherwise (none lacking) 108

Computer Program 20 Check on Missing Data (IACK) MAD (17 MAY 1967 SIN PROGRAM LISTiTN....... LActK. - - Lc;,K3,, Ltk4., L EXTERNAL FUNCTION TVALUEI-;-VA-LUE2-E-,-VAVAUE3,tVU ALU E 5T DEFINE UNARY OPERATOR.LACKS., PRECEDENCE SAME AS *E. ~MODE STRUCTURE 2 =.LACS ---- -7.. JMP *+18,AC,*+1 J3M P -4-. -- T ~ ~ I- ":'-'' -..........'...'... JMP *+1,LA,*+18 JMP *+1,BT,*+-8 -......... LAS =4K1 TRA TRA — PXD -- TRA CL --- nilT LOC+3 LOC+3 LOC+2 A C SLW T --------- - JMP *+8 JMP. *+ 1,BT'S-...+3 XCA JMP *+6 STQ T iJMP *+3 JMP STO CLA CAS TRA TRA PXO *+2, BT, *+ I B =4K 11 LOC +2 LOC+3 0,0 TRA L+2 --—.-.. --- ——.-.CLA =1 END ENTRY TO LACi. WHENEVER.NOT..LACKS. VALUE5 ENTRY TO-A-CK4.K ----- ---- - - ~ - WHENEVER.NOT..LACKS. VALUE4 eNIRY — Y LACK-3- -. WHENEVER.NOT'.LACKS. VALUE3 ENTRY TO LACK2. WHENEVER.NOT..LACKS. VALUE2 ~ENTRY TO LACK. - -. — -- ------- FUNCTION RETURN.LACKS. VALUE1 END OF COND T ION -- ----------- —. ---. END OF CONDITIONAL END OF CONDITIONAU. END OF CONDITIONAL FUNCTION RETURN TB END OF FUNCTION (THE NUMERIC FORM OF THE OPERATOR-MODE ARGUMENT IS M' t -L = *L'AbKS. U U - 11400 ) 109

Computer Program 21 Title: Rounding of Numbers RNDOFF (VALUE, TD) IROUND (VALUE) Purpose: RNDOFF, to find a round off of a value IROUND, to find the nearest integer of a value Arguments: VALUE = value to be rounded. TO = precision of the round, off (e.g. 1.0,.5,.1) RNDOFF = rounded value IROUND = nearest integer 110

Computer Program 21 Rounding of Numbers (IROUND) D.i. J M.A V.1~ 67 VE S $LkN) PR RAL t SI NG...... RN o ' FF, ) tuua, EXTERNAL FUKTAGIN (VALUEtTO) INTIELER dHGLE bOLLEA-.. fLtAT ENTRY JO RHXFF, FLLAT 18 RUMUT1 =.ASo. TO TRANSFER TO SKIP ENTRX JT IRORiND. -LGA I = 8 RONDITO = 1. YK 1P ANSiiR = VAL&JE WiHNEVER ANSiER.NE. O. h-HGLE = ANSWER/RCNDT':O +.ABS. ANSWiER/ANSWER + ANSWER) tOLLE _. + WHGCLE WHiENEVER -.NiT. FLOAT, FUNCTION RETURN WHOLE ANSWER = i-HGLE*R-GNOTO ENL G"F C'LNDI IONAL FUNCTiLN RELTURN ANSWER EN:L OF FiN.hCTILON 111

Computer Program 22 Title: Axes Plotting AXIS (XO, YO, AXLTH, THETA, AXSCAL, HGTH, TITLE) Purpose: To either plot an axis (with tic marks) (with or without numbering) or to plot a centered. title or both/neither. Arguments: XO, YO = coordinates in in. of the beginning of the axis AXLTH = magnitude is the length of the axis in in., if positive, it is plotted from beginning to end., if negative, it is plotted from end. to beginning. THETA = counterclockwise degrees inclination from horizontal (0) = value of axis variable at beginning of axis AXSCAL (1) = increase of axis variable per tic mark (2) = in. per tic mark on axis.. HGHT = magnitude is height of numbers and. letters in in. if positive, they are above the axis, if negative, they are below the axis (0) = 0 to d.elet axis (D) = format for axis numbering (2-5 character BCD) (1) = no. of characters in title (INTEGER) (2)... = title to be plotted (BCD string) Graphics: Tic marks will be.075 in. on the side opposite title. Centerline of numbering will be HGHT from axis. Centerline of title will be 2.5*HGHT from axis. The numbering is centered. about the 3rd. position from left. 112

Computer Program 22 Axes Plotting (AXIS) MAD (17 MAY 1967 VERSION) PROGRAM LISTING..... EXTERNAL FUNCTION AXIS. XO~YOAXLTHiTHETA,AXSCALtHGHTTITLE) INTEGER NUMDIV, TITLE, FMTt NCHAR, CENTER9 I BOOLEAN PLTAXI, PLTNMR, PLTBCOt GNEND, LACK. FNT = TITLE PLTAXI = FMT.NE. 0 HEIGHT = HGHT PLTNMR = HEIGHT.NE. O. WHENEVER PLTNPR NCHAR =.ABS. TITLE1 ) PLTBCD = NCHAR.G. 0 OTHERWI SE PLTBCD = OB END OF CONDITIONAL WHENEVER PLTAXI.CR. PLTBCC LENGTH = AXLTH DELREL = AXSCAL(1) DELTIC = AXSCAL(2) BGNEND = LENGTH.L- 0. WHENEVER BGNEND LENGTH = - LENGTH DELREL = - DELREL DELTIC = - DELTIC END OF CONDITIONAL DEGREE = THETA RADIAN = DEGREE/57.29577951 SINE = SIN. (RADIAN) COSINE = COS. ( RADIAN) XASS = XO YABS = YO XEND = XABS + LENGTH*COSINE YEND = YABS + LENGTH*SINE NUMDIV = (LENGTH +.0001)/.ABS. DELTIC ABSHGT =.ABS. HEIGHT WHENEVER PLTBCD CENTER = (NUMDIV + 1)/2 XDEL = - (NCHAR/2)*.8571428571*ABSHGT YDEL = 2.5*HEIGHT -.5*ABS&hGT XBCD =.5*(XABS + XEND) XDEL*COSINE - YDEL*SINE YBCD =.5*(YABS + YEND) + XDEL*SINE + YD9LAC"SINE END OF CONDITIONAL WHENEVER PLTAXI WHENEVER PLTNMRXDEL = - 2.*ABSHGT YDEL = HEIGHT -.5*ABSHGT XNMR = XDEL*CCSINE - YDEL*SINE YNMR = XDEL*SINE + YDEL*COSINE XREL = AXSCAL FMT = FMT.RS. 6.LS. 6.V. $00000*$ END OF CONDITIONAL XTIC =.075*SINE YTIC = -.075*COSINE WHENEVER LACK.(HEIGfT - HEIGHT) XTIC = - XTIC 113

Computer Program 22 (Concluded) YTIC = - YTIC END OF CONDITIONAL XDEL = DELTIC*COSINE YDEL = DELTIC *SINE I = 0 WHENEVER.NOT. BGNEND PENUP. (XABS,YABS) OTHERWISE PENUP. (XEND,YEND) NUMBER = NUMOIV WHENEVER PLTNMR, XREL = XREL - NUMBER*OELREL XABS = XABS - NUMBER*XDEL YABS = YABS - NUMBER*YDEL NXTDIV PENDN. (XABS, YABS) END OF CONDITIONAL PENDN. (XABS+XTIC,YABS+YTIC) WHENEVER PLTNMR PNUMBR.(XABS+XNMR,YABS+YNMR,ABSHGT,XREL,DEGREE,FMT) XREL = XREL + DELREL WHENEVER I.E. CENTER.AND. PLTBCD PSYMB. ( XBCD,YBCDtABSHGTT ITLE (2),DEGREE, NCHAR) PLTBCD = OB END OF CONDITIONAL END OF CONDITIONAL PENUP. (XABSYABS) WHENEVER I.L. NUMDIV I = I + 1 XABS = XABS + XDEL YABS = YABS + YDEL TRANSFER TO NXTDIV END OF CONDITIONAL WHENEVER.NOT. BGNEND, PENDN.(XEND,YEND) OTHERWI SE PSYMB. (XBCD,YBCDtABSHGTTITLE (2),DEGREE, NCHAR) END OF CONDITIONAL END OF CONDITIONAL FUNCTION RETURN END OF FUNCTION 114

Computer Program 23 Title: Curve Plotting GRAPH (SCALES, XTITLE, YTITLE, TITLE) Purpose: To prepare a graph for data plotting, including output media specifications, coordinate system quantification axes with respective titles and numbering at tic marks, and an overall title. Argument s: (0), (1), (2) = AXSCAL for X axis (3), (4), (5) = AXSCAL for Y axis see XTITLE = TITLE for X axis AXIS YTITLE = TITLE for Y axis (0) = no. of characters in overall title (INTEGER) TITLE TITLE (1)...(N) = overall title (BCD string) Graphics: The axes are chosen to begin at (.65,.41) in. No. of X divisions are such as to use most of 14.000 in. No. of Y divisions are such as to use most of 10.333 in. The border with tic marks is completed on the other 2 sides. Numbering and. lettering are done with a height of.13 in. TITLE is treated. as a 2nd YTITLE. The above restrict XTITLE to 125 characters (23 words), YTITLE to 92 characters (18 words), TITLE to 92 characters (17 words). 115

Computer Program 23 durve Plotting (GRAPH) MAD (17 MAY 1a67 VERSIUN) PRCCGRAM' I ST I NG 0 0 0 GVRAP 14. EXTERNAL FUNhCTION CRAPH.(SCALES, XTITLE,vYTITLETITLE) VEC TOR VALUES YFMT( 1 ) 0..... INTEGER NUMDIV, NCHAR, YTITLE, TITLE PLTPAP. ($400) PLTXMX.(14.90) XTIC = SCALES(2! YTIC = SCALES(5) PLTOFS. (SCALES, SCALES ( 1 )/XTICSCALES ( 3 ), SCALES(4)/YTIC,.65t.41) NUMDIV = 14.CCO1/XIIC XLTt = \UMDIV*XTIC NUMDIV = 10.3334/YTIC YLTH = NUMDIV4YTIC YFMT = YTITLE AXIS.(.65,.41,i XLTH0., SC A L E S, -. 1'3, XT I TLE) AXIS.(XLTH+.65,.41,YLTH,90.,SCALES(3),-.13,YFMT) AXIS.(. t 5,YLTHf+.41,-XLTHO., SCALES, O., XTITLE) AXI S.(.65,.41,-YLTH,9O., SCALES(3),. 13,YTITLE) NCHAR = TIiTLE WHENEVFR, NCHAR oG. C, PSY'M6',{(.195,.41+YLTH/2.-(NCHAR/2)*.1ll14285'714,.13, TITLE(1),90.,NCHAR) FUNCTIGON RETURN END OF FUNCTICN 116

Computer Program 24 Title: Results Punching (PUNCH) Purpose: To punch a given sequence of points according to a given format. Input: Sequence of values that are required to be punched. 117

Computer Program 24 Results Punching (PUNCH) MAD i.17 MAY 1967 VERSI ON) PROGRAM LI STING...I N.. PLANC.I. EXTERNAL FUNCTION PUNCH.(RUN,ID,.BEFORE,NADD,VALUES) NORMAL MODE IS INTEGER FORMAT VARIABLE FV ADDS = ADD ADDTEN = 10*ADOS IEND = N*ADDS FV = 7 - BEFORE PUNCH FORMAT $14,I12C4' FV'P10F7*$, -1 (I = 0t ADDTEN, I.GE', IEND RUN, CARD.(I), ID, 2 (J = I, ADDS, J.E. JEND, VALUES(J )) FUNCTION RETURN INTERNAL FUNCTION CARD. JEND = I + ADOTEN WHENEVER JEND.G. IENDt JEND = IEND FUNCTION RETURN 1 + i/ADOTEN END OF FUNCTION END OF FUNCTION J-18

APPENDIX B TABLES "ig

TABLE 1 EFFECT OF ENGINE SPEED ON IGNITION DELAY USING CITE FUEL AT A MEAN PRESSUE OF 500 PSIA-DURING THE IGMTON DELAY HF'\) 0 I~TA SET A4A HAS 5.RUNS~ THE ATAC ENGINE. ( SLEEVE, IVC @ 128. DBTOC! USE~ CT1c FUEL (3. COC PSI), MD~3 OIL, AND H2C CeCILANT,, FC'-R USE SPEEC ~LOAD FUEL AIR BLOW ROOM-SURGE-2. IVC'2IkJ-RIS DBTDC AT START CF /~IR IVILLVCLTS EXEAL, ST RUN W 0 R PM LBS MIN L/HR PSI6 F CFPP INFG INHG PSI FSI PSI LIFT RISE ILLUP F MIN INC F F~ 71 E C 1000 21.8 8.!7.18 34~0 75.6 28.9 i0.7 3.1 436 213 20.7 11.3 9.4 9~ -.C-~00 622 14 72 ~ C 1500 17.8 5~96 ~30 51.2 73 ~~ 29.1 6.8 3~3 401 276 21.0 8~3 6.0 S] -.O-.OO 657 49 73 C C 20{.)0 13.1 5.01.27 66.E 76 ~E 29.2 3.6 4~0 386 312 20.9 5.1 2~E c4 -.0-.00 691 51 74 E D 2400 1!.O 9.12.ZS 51.5 76.E 29.1 1.5 2.g 360 316 21.4 3~3 -~C c3 -~0 -.00 699 52 70 g D 2800 9.5 3.73 ~25 57.6 78-.C 2'9.3.0 2~7 360 288 20.5 1.2 -~C Cl -.0 -~00 746-0 MEAN 1940 14.6 6.40.26 52.2 76.7 29.! 4.5 3.2 369 281 20.9 5~8 6.0 c3 -.0-.00 683 42 ERRS 637 4.5 1.95.04 10.7 2.i.1:~8.4 28 37.3 3.6 2.8 2 -.g -.00 42 16 FCR CR/~NKC~SE OILS COCLANI SYSTEM CYL HD W/~LL TEIVF RUN ~ CUT(F) INC CPS OUTIF) INC INHG [NI'.JF) EXH.(F) 71 -~0 -~0 -0 leS~g -~0 -~0 -.0 -~C 72 -.C.0 -O 171.C -.C, -.0 -.C -.g 73 -.0 -.D -0 172.C -.0 -.0 -.0 -.C 74 _.n -.0 -0 171.O -.C -.0 -.0 -.C 70 -.0 - 0 'O 17n. C -.O -.C ~ - 0 ~., -, —. '.u. MEAN '-.0-..0 -0 17.,0.4 -.0 -.0 -'.C -.0 ERRS -.O -.C -O 1.4 -.0 -.O -.0 -.O ENGINE WITH 16 69/1 RATIO HAS q.5610 CUIN CLEARANCE. FUEL WIIH 1.999/1 RATIO Iq~S 48,84 LBM/CLFT (@6C) AND LIBEF/ITES 18700 BTU/LBI"I. FOR ER~KE PMEP -BSFC FUEL/ CYCLE[LBMIlOO0) SLRGE EFF ~IVC AI START OF Ii~JECTI'CIk 'IYE[~/~GE[ [UR[NG I~EL~Y DEL/~'~JPEECI I~I~.LLIF) RUN HP PSI #/HRHP fiIR AIR BLO~ EXH PSIA PCT F:INDEX PSIA #/CLFT R INDEX PSI~ #/CUFT R PRISE ILLE:M MIN INC 71 7.3 80.4.4E4.C519 3.52.08.12 19.4 90.2 170 1.387 45~.847 144'1 1.193 5~3 1.CO~ 14~ 1.567 1.~E3 -~ -0 72 8.9 65.7.5C9.~313 3.21.05.11 17.6 8g.g 182 1.390 422.763 1473 1.23.4,~5S.958 1549 1.411 1.667 -O -O 73 8.7 48.3.634.0310 2.98.05.Cc 16.1 ~1.7 206 i.388 406.7C9 1526 1.227 5~.~3C 1619 1.317 ].525 -C -(] 74 8.8 40.6.6cC.0315 2.70.05.oq 15.0 68.9 195 1.420 378.631 1598 ].204 54~.85~ 1696 1.257 -.000 -~ -0 70 8.9:35.0.860.0359 2.53 -.gO.0~ 14.4 E6o6 208 1.419 377,610 16491.169 541.830!733 1.149 -.000 -(] -0 MEAN 8.5 54.0 631.~323 2.99.06.1~ 16.5 89.5 192 1.401 408.712 1537 1o205 555.91~ 1617 1.340 1.692 -C: -O ERRS 6 16.8.141.0019.36.O1.01 1 8 1.7 14.015 30.0e7 77.024 ]C 065 90.142.147 -C -0

TABLE 2 EFFECT OF ENGINE SPEED ON IGNITION DELAY USING CITE FUEL AT A MEAN PRESSURE OF 700 PSIA DURING TEE IGNITION DELAY F-H PO DATA SET A4B _HAS 5 RUNS. 'THE ATAC ENGINE ( SLEEVEt' IVC @ 128 DBTDC) USE~ CTiS FUEL (3C0C. P.S-IIs MDV30]Lt-Al~O EGLY CCOLANTo' FOR USE SPEED LC]AD FUEL~ AIR BLCW ROOM-SURGE-@IVC-2INJ-R[S DBTDC AT START OF AI!~ PILLWELTS E XIdAUST RUN W 0 RPM LBS MIN L/HR PSIG F CF)N INHG INHG PSI PSI PSI LIFT RISE ILLU!V F MIN INC F I~b 86 E C 1000 27.6 5.74.5~ 48.5 76.7 29.2 22.9 1.1 552 212 20.8 ~13,6 -.0 96 12.1 1.13 7E9 72 87 E C ~1500 26.6 8.74.57 73.0 81.7 2-9.3 18.7 1.0 532 276 20.8 1.1,0 -.0 S~ 13.4 1.15 813 40 88 E D 2000 ' 22.9 6.'95.60 67.5 79? 29.2 15.1 1;0 513 340 20.8 8.0 -.0 c, 5 14.3 1.01 843 49 89 E E ~2500 18 8 5 82.79 67'.1 80.1 29.3 12.7' 1.0 513 363 20.5 5.8 -.C c3 14.3.82 8i3 52 90 E E 2899 13.9 5.52.80 72.2 82.c 29.1 10.6 3.0 477 370 21.0 5.1 -.0 101 14.4.40 931 60 MEAN 1980 22.0 6,51.66 65:7 80.7 29.2 16.0 1.4 517 312 20.8 8.7 -.0 c~ 13.7.90 850 54 ERRS 679 5.1 1.13.11 8.9 2.1.1 4.4.8 25 60.2 3~2 -.0 _~.9.28 49 11 FOR CRJ~NKC~SE OILS COOLANT~ SYSTEM CYL HD WALL lEIV~ RU!~ OUT{F) INC CPS OUT(F} INC INH~ INT.{F) EXH,{F} 86 178.2 2 2 49 178.8 7.0.8 269.2 325,~ 87 195.2 2.2 55 176.7 5.4 2.0 264.0 236.B 88 205.2 2.2 60 176.2 4.3 3.7 264.9 350.1 89 207.1~ 4.9 67 175.9 4,1 5.9 2~8.5 35].8 ~0 2~11.1 7.8 80 171 5 2.5 8.3 270.7 360.8 MEAN 199.q 3.9 62 175.8 4.7 4.1 26.7.5 345.C ERRS 11.~ 2,2 ' 11 2.q 1~.5 ~2.7 2.6 12.3.. ENGINE WIT'H 16.69/1 RATIO HAS q.56t0 CUIN CLEARANCE. FUEL WITH 1.999/1 RATIO H~S 48.84 LBIV/CLFT {@60) ~ND LIBEl;ATES 18'/.00 BTU/LBMo.~ FOR ER/~KE 8MEP PSFC FUEL/ CYCLE{LBM/100(.)) SURGE EFF ~IVC AT START CF IhJECTIC!~ ~VEI~;~C-E~ ~UR[~G EEL/~Y CELA~{MSEC) IiALL(FI RUN HP PSI #/HRHP AIR AIR BLOW EXH PSI A PCT ' F INDEX PSIA #/CUFT R II~D~X PSI~ #/CUFT R' PRISE [LLI~N MIN INC 86 9.2 101.8.467.0310 '4.61.09.14 25.6 89.6 113 1,418 57~ 1.101 1395 1.2~5 '~E2 1,25~ '1436 -1.200 -.O(](} /,35 3? 87 13.3 ~98.1.454.0314 4.27.06.12 23.6 90.2 109 1.439 557 1.019 1450 1.209 691 ] 219 1503 1.089 -..000 4~77 3? 88 15.~ 84.5.498.0315 4.02.05.11 21.8 c, 1.7 101 1.4'57 536,9561488 1.203 '/Cc 1.200 15,:5 1.067 -.000 50~ 33 89 15.7 69.4.571.0315 3.78.04.1G 20.6 90.7 107 -1.472 535.910 1561 1.177 921'1'171 1630.c, 80 -.000 50E 27 90 13.4 51.3.7(]6.0316 3.46.04.OS 19 5 89.C185 1.434 499.816 1628 1.1.81 6Cl 1.'072 1707.914 -.00G 509 13 MEAN 13.4 81.0.539.0314 4.(]3.06.11 22.2 90.2 123 1.444 541.9~0 1504 1.199 69E ],184 1566 1.C50 -.OCO 487 29 ERRS 2.3 18.8.093 9002.40.02.-02 2.2 9 31.019 ' 26.096 8.2..018 14.063 S5.098.000 28 9,... FCR' CRaNKCASE OILS COOLANT SYSTEM RUN GPM BTU/SEC ~ GPM BTU/SEC 86 3o4g 5 2.2 6.0 4.0 18.I 87 3.91.5 1.7 8.9 4.6 14.6 88 4.27.6 1.5 11.8.~4.6 12.3 89 4.77 1.5 3.2 14.'7 5.8 12.4 90 5.69 2.8 5.7 17.4 4.1 8.4 MEAN 4,43 ~.1.2 2.9 11.8 4.7 131 ERRS.76.9 1.5 4.0 6 3.2

TABLE 3 EFFECT OF COOLANT TEMPERATURE ON IGNITION DELAY F. R) R) DAT~ SET AS~ HAS 8 RUNS. THE ATAC ENGINE ( SLEE~fE, [VC @ 128 DBTDC) bSEO CT1S FUEL (3000 PSI}, MOV3 OIL, ~ND EGLY COOLANT. FOR!JSE SPEEC L8~D FUEL AIR BLCh t;00N-SIJRGE-@IVC-~IKJ-RIS OBTGC /~T STa~T OF /~IR ~ILL~/CLTS E)~FAI. ST RUN W 0 RP~ LBS MIN L/HR PSIG F CFP~ I NHG INHG PSI PSI PSI LIFT RISE [LLU~ F MIN INC F IqU 75 E E 2000 27.6 5.65.76 71.0 75 8 28.9 40.2 7.5 778 338 21.0 12.8 -.0 253 -.G -.00 848 60 76 E E 2002 26.5 5.68.81 76.8 76 1.O 28.9 40.2 5.9 774 342 21.0 12.8 -.0 255 -.C-.00 840 59 80 E E 2900 28.3 5.53.84 71.4 85 1.C 29;'3 40.1 6.8 780 338 21.0 13.0 -.0 253 -.C -.OO 905 5(: 7c3 E E' 2000 27.2 5.50.88 71.4 84 1.C 29.3 39.9 6.8 774 341 21.1 13.0 -.C 252 -.0 -.00 902 54 78 E E 2C)00 27.1 5.53.90 71.1 84 1.1 29.2 3~.9 8.7 774 333 20.9 12.9 -.0 25.: -.C -.00 913 58 77 E E 2000 24.4.5.54.91 70.9 84 1.1 29.3 40.2 8.2 782 339 20.9 12.7 -.0 257 -.C-.00 921 74 81 E E 1999 28.9 5.51.92 71.1 79 1.C 29.4 40.0 8.4 760 350 21.0 12.5 -.0 253 -.C -.00 950 4e 82 -0 22.8-.00.95 -.0 -0.~ -.0 -.0 -.0 -0 -0 -.0 -.0 -.0 -C-.0 -.OC -0 66 MEaN 2000 26.6 5.56.87 71.1 81 1.C 29.2 40.1 7.5 775 340 21.0 12.8 -.0 2f4 -.0 -.00 897 59 ERRS t 1.9.06.06.2 4.1.2.1.9 7 5.1.2 -.0 2 -.0 -.00 37 7 FOR /RANKC/~SE OILS CJJFJLANT SYSTEM CYL i-O ~ALL TEMP RUN OUT(F) INC CPS OUT(F) INC INHG INT.{F) EXH.(F} 75 192.5 3.5 72 156. ~ 6.6 3.7 -.0 -.0 76 199.3 3.1 73 187.0 6.0 3.8 -.0 -.0 80 20~.g 4.0 73 217.0 5.6 3.5 -.0 - 0 79 206.S 4.4 75 246.C 4.8 3.6 -.0 -.0 78 209.0 6.0 77 27~.1 4.7 3'.6 -.0 -.C 77 210.5 7.1 76 3'04.3 2.0 3 6 -.0 -.0 81 211.8 7.7 75 305.0 3.3 3.g -.0 -.0 82 -.O -.0 -0 -.O -.0 -.0 -.0 -.0 MEAN 2Of.] 5,1 74 241.7 4.8 3.7 -.0 -.0 ERRS d.4 1.7 2 53.4 1.3.1 -.(~ -.C ENGINE WITH 10,.~:g/1 RATIO HAS 4.5610 CUIN CLEARANCE. FUEL WITH 1.999/1 RATIO H~S 48.84 LB~,/CLFT [@60) ANE LIBEi~ATES 18700 BTU/LBM. FGF ER~KE EMEP gSFC FUEL/ CYCLE(LBM/ICOC} SLRGE EFF glVC /~T START OF Ib, JECTICi~ ~~EF/~C-E~ ~URI.NC-' CEL~Y ~EL~YIIVEC) kAL. LIFJ RUN HP PSI #/HRHP AIR AIR BLOW EXH PSIA PCT F INDEX PSIA #/CUFT R INDEX PSI~ #/CIOFT R PRISE ILLIOM MIN INC 75 18.4 101.8.506,C312 4.96.05,i7 33'.9 93.5 360 1.3El 819 1,162 1832 1,197 S64 1.37~. 18~5,~83 -,CCC -C -0 76 17.7 97.8.520.0319 4.9z,.07.18 33..9 g3.3 332 1.396 814 1.177 1827 1.216 9EC 1.371 1885.683 -.000 -0 -0 80 18.9 104.4.4c8.9316 4.95.07.17 34.1 92.8 352 1.388 821 1.178 1841 1.222 c,~5 1,367 ISCO.~67 -.00C -C: -0 79 18.1 100.3 518,0316 4.96.07.17 34.0 93,1 349 1.388 815 1.174 1833 1.223 9~~ 1.366 1893.675 -.000 -0 -0 78 18.1 100.0.515.0314 4.94.07.17 33.9 93,2 389 1.364 817 1.178 1831 1,215 979 1,367 1888.f:67 -.OGO -0 -0 77 ~6,3 90.0.569,0313 4.93.07.17 34.1 92,8 385 1.371 824 1.176 1852 1.1~7 989 1,369 19C5.683-.000 -0 -0 81 19.3 106.6.483,t1312 4.97.07.1~ 34.1 9'3.1 382 1,360 802 1.180 1797 1.216 973 1,382 1856.709 -.OCC -C -0 82 -.0 E4.1 -.000-.,)000 -.00 -.OO -.0C -.0 -.0 -0 -.000 -0 -.000 -0 -.OO0 -C -.000 -0 -.00C -.0~0 -C -0 MEAN 18.1 98.1.516.0313 4.95.07.17 34.0 9:_.1 364 1.378 816 1.178 1830 1.212 981 1,371 1888.681 -.0C0 -C -0 __ER~ g 7 0._0_,025:)go2.01.01.OC.1,2 20.013 6.002 16.010 5.005 15.013-.00C -0 -0 FOR CR~NKC~SE nILS CO6LANT SYSTEM RUN GPI~ EIU/SEC % GPM ETU/SEC % 75 5.12 1.1 2.4 11.9 7.4 15.3 76 5.20 1.O 2.1!1.,9 ~.g 14.4 80 5.20 1.3 2.7 11.4 ~.3 12.8 79 5.34 1,5 3.0 11,6 5,~ 11.3 78 5.48 2.1 4.3 1'1.5 5.5 11.3 77 5,41 2.4 5.1 11.5 3.4 7.1 81 5.~4 2.6 5.4 12.0 4.0 8.4 82 -.00 -.0 -.0 -.0 -.0 -.0 MEA~ 5.20 1.7 3.6 11.7 5.6 1i.f ERRS.12.6 1.2.2 1.3 2.8

TABLE 4 EQJIVALENT AREA FOR FUEL FLOW IN INJECTOR NOZZLE VERSUS NEEDLE LIFT (Results of Computations)-(See Fig. 23) H3 RD ~$r- uI- 11~ldt::t.,I ltJl~i = Ut..ht, M/-~KOt:: t..U!7..I-I-t!..J.t:l~l ~ t::kt. JtVALf'-NI PKt:.e ~ b~KI.II"UI::L UE!~..~llY ~ II"Ut::L I'JKI::5..~UKl'" - t,~LINUI::K I"Kt::~bUKIr. I I! *I~.D.,t~D (LBN/HOUt~) S(; [N/].G0000C (LBM/CLFT) (PS[A) (PSIA) INJECTOR HAS FOUR ~01181 INCh ~OLE~9 COhlA~T SUEFACE H.a$ ~[AFETEt~$.C7320 & ~13'750 AND HEIGHT ~05389, TIP ~ANGLE IS 66.50 CEGREES ECUI~~LENT.~Ri:/~ = 1/5C4RT,(L/IOL1LET.~REA fCF hEEDLE ~ SE4TI.F~2 + ]/(ARE~ CF EOLES).P~2 - (DISCH.4RCE COEFFICIENT/AREA GF EOD~I.P.2) PlLSiq 12b~J - '.~04b*MiL$) ~38.2 4208.4 A S~U~I: utScii.~F, Gf ~LEFFiCiE~~ =.7000 EQUIVALENTAREA (SQUARE INCFES/1000000) FOr EYE~Y.05 NIL LIFT (MIL= INCH/10001 FRCP.00 TG 30~00 NILS ~ILS.00.05 ~10 ~15.26 ~25.30.35 ~46.45 -,50.55 ~60.65.70. ~75.80.85.90.95 1.00.OO ~0 ~.3 12.~ l~.'~ z~.2 3i.~ ~~~ 43.~ 50.C ~e.1 b2.2 e~.3 74.3 80.3 8b.2 92.i 97.9 103'C 109.3 i14.~ i20.5 1. OC 120.5 126.6 1'31.5 136.8 142..1 147.3 152.5 157.'6 1~2.6 167.5 172.4 177.1 181.8 186.5 191.0 191~5 199.9 204.2 208.4 212.6 216.6 2.00......ZI~,6......226.i 224J0 —228.~ 2~2J. 2 2~b.~ 239.b 243.2 2~b.t 21C.i 253.5 25~.7 260.-0 —2-63~1 28b.2 26~..3 272.2 275.1 278.0 280.8 283.5 -32C~2 322.1 324.0 325.8 327.6 4.00.....327 ~ 229~3-331 i ~5Z.~7 ~54 4 ~3~.-T 3~7;~ —~9 1 ~40~%-~4Z 1 3~,6 3~b 0 34~J4 347.8 5~9.1 ~C 4 351 7 ~53 ~ 354 2 355.4 ~56.6 5.0C 356.~ 25~.~ 35~.9 2~0.0 261.1 362.2 3~2.3 364.3 2~5.= 3~.3 367.3 _=~.3 369.2 370.1 371.0 371.S 372.8 373.6 374.5 3~5.3 376.l ~.00 376.1 31~.9 37?~7 318.5 ~19.2 ~0.~ -~c.? ~L.~ 3~Z.i ~2.~ 383.~/3~.i 38~.~ 388.4 3~.1 3~t.? 3~7.3 38?.9 388.~ 389. i 389.7 7.00 389.7 39C.2 396.a 391.3 ~91.~ =32.4 392.6 3c, 3.4 363.S ~~4.4 394.S7335.3 395.8 396.3 396.7 397.2 397.6 398.1 398.,~ 398,$ 399.3.... 8,0-0 —399,,3 399.?-406.1 400.5 400.5 qOI.3 46~i.7-%~I2~qI~62.q qC2.~ 403 i 403.5,03.8 z, 0-4.2 404.5 '~C4.8 405.2 405.5 405.8 406.i 406.4 9.00 406.4 40c.7 407.0 407.3 z:OT.f 407.S 468.2 40~.5 408.7 4CS.C 40g.3 409.5 409.8 410.1 410.3 41C.~ 410.8 411.1 411.3 411.5 411.8 10;00-4Ii.8 —~Tz.~C-W/2.2-4i2JS —~i2,? 412.~zI~.I4I~3-413.! 41~.~ ~iI.~ ~i4.2 ~14.4 ~,i4.b 4i~.~ ~i~.0 4ii.i ~15.3 4i5.5 415.7 415.9 11.00 4.15.9 41~.1 416.2 41~.4 416.~ 410.8 4i~.S 417.1 417.~ 417.4 417.6 417.8 417.9 418.1 418.2 41~.4 418.5 418.~ 418.8 419.0 419.1 -I~0U-419.1 41~.3 4is.~ 419.t 419.1 il~.t 42(3.0 4zo.1 ~zo.2 426.~ ~20.b ~ZO.6 4zu.7 ~20.9,21.0 42i.1 ~2i.2 42i.~ 42i.5 421.6 42i.7 13.0C 421.~ 421.8 421.9 422.1 4'22.2 422.3 422.4 422.5 422.e 422.7 422.8 422.9 423.0 423.1 423.2 42.3.3 4-23.4 42.3.5 423.~ 423.~ 423.8 i4,06......423,~-42~.-9-424.C —42~I q2qT. 2 ~24J2 qZq~.~ ~2~.5 42~.~ 42~ ~ 424.1 ~24.8 ~24.9 v~25.0 425.i 42~.i 425.2 425.3 z, 25.4 425.5 425.5 15.0C 425.1 425.6 42~.7 425.6 425.8 425.9 z26.0 426.1426.1 426.2 426.3 426.4 z, 2~.4 426.5 426.6 42~.~ 426.7 426.8 426.8 426.~ 427.0..... I6~06 427,C....427.C-q2T. T 42W%~~.2-q2-T;~ ~2T~4 42T. 4 427.~ ~21.5 427.~ ~27.7 ~,27.? ~27.8 42?.8 ~2i.~ 428.0 428 C, -,28.i 428.1 428.2 17.00 428.2 428.2 428.3 428.3 428.4 428.~ Z28.~ 428.6 428.~ 42~.7 428.7 428.8 428.8 428.9 428.9 423.C 429.0 429.1 429.1 429,2429.2 18.064 —23-.2~23.3 ~,26.3 429.3 429.4 q-25.4 z29.~ 429.5 429.t 423.t ~2~.7 425.?,2~ ~ ~2~.8 ~2.~ 8 ~2c.~ ~,2~.9 ~30.C,30.(. ~30.0 ~30.'1 19.06 430.i 430.1 436.2 430.2 430.2 430.3 4~0.3 430.4 430.4 430.4 430.5 436.5 430.6 430.6 430.6 4~C,~ 430.7 430.7 430.8.4'30,8 430.8 20,00 436.8 436'~9 —436;~43lY.~ ~FI~C~3~.~-4;1.i 431~1 431.1 431.2 4~l.Z 4~1.2 43i.2 43i.~ 4~1,3 43i.3 4~i.4 ~i31.4 i3io4 43i.5 ~t~1e5 21.00 431.5 431.5 431.6 431.6 431.~ 431.7 Z2l.? 431.7 431.7 4.31.8 431.8 431'8 431.9 431.9431.9 431.S 432.0 432.C 432.0 432.1 432.1 22,0() 4~2.1 432.U4::,~.~~2-.2 —~321Z~-(3ZJ2 432.2 432.~ 432.3 4~2.3 432.~ 4_t2.~ 4~2.4 432.~ 452.~ 432.~ 432.5 ~32.5~32.5 432.~ 432.6 23.0C 432.6 43.2.6 432.e 432.~ 432.~ 432.] z~2.7 432.7 432.8 432.8 4.32.8 4.32.8 432.9 432.9'432.9 432.9 432.9 433.6 433.0 4.33.0 433.~ 24.06 4-3.0 4'33.1 433.i 433.1 433.1 ~33.~1 433.2 453.2 4JJ.2 43'3.2 433.2 4~3.5,53.3,53.~ 433.5 ~3~.3,,3~.~ i33.~1 Z, 33.-, ~t33.4 433.4 2.5.00 433.4 433.4 433.5 433.5 433.5 433.5 Z':.5 433.6 433.6 43:.6 433.6 433.~ 4'3,3.6 433.7 433.743~.7 433.7 433.7 433.8 433.8 433.8,~4.0 43,.0 ~3~.0 ~3~.~ ~34.0 ~3~.i ~34.i 43~.i ~34.1 27.00 434.1 434.1434.1 434.1 434.2 434.2 434.2 434.2 434.2 4~4.2 434.3 434.3 434.3 434.3 434.3 4.34.3 434.3 434.4 434.4 4.34.4 434.4 28,00 434;~-434,4 —434.4 434.4 434.~ Z[34.5 4~4.5434.5 434.5 434.5 434.5 454.5 %~4.5 ~34.b *~*.b ~34.e,34o~ 434.6 q3q.~ 434.~ 434.7 29.00 434.~ 434.? 43-4.7 434.? 434.7 434.7 434.7 434.7 434.7 4:4.8 434.8 434.8 434 8 434.8 434.8 434.8 434.8 434.S 434.9 434.~ 434.~

500 o 4500 AREA OF NOZZLE HOLES 'o 4 5 0 - - - - - - - - - - - - - - - - - - - - - - X LU 400 -z "r' - 350 / LLU C300/ H 200: <:I z 50 0 L n __ 0 2 4 6 8 10 12 14 16 NEEDLE LIFT 0 CD U) - - - - - - - - - - - - - - - - - - - INJECTOR NOZZLE ADB- 1505/77-3612 _!. 2 _2, 2 2 18 20 22 24 26 28 Fig. 25. Equivalent area for fuel flow in injector nozzle versus needle lift.

APPENDIX C REFERENCES 1. Bolt, Jay A. and N. A. Henein, "Diesel Engine Ignition and Combustion, University of Michigan, ORA 06720-8-P. 2. Jost, W., Explosion and Combustion Processes in Gases, McGraw Hill Book Co., N. Y., 1946, p. 239. 3. Andreev, E. A., Acta Physiocochim (*USSR), 6, p. 57 (1937), c.f., B. Lewis and G. Von Elbe, "Combustion, Flames and Explosions of Gases," Academic Press, N Y, 1961, p. 145. 4. Aivagov, B., and Neumann, M. B., Physik Chem., 1936, B 33, p. 349. 5. Small, J., "Vagaries of Internal Combustion," Engineer (London), 164, 1937 642.668. 6. Lee, D. W. and Spencer, R. C., "Photomicrographic Studies of Fuel Sprays," NACA TR. 454, 1933. 7. Rothrock, A. M. and Waldron, C. D., NACA report 561, 1936. 8. Miller, C. D., "Slow Motion Study of Injection and Combustion of Fuel in a Diesel Engine," SAE Trans. 53, p. 719-7355, 1945. 125

UNlVtK~.11 IrUV MILMlUAN 11 9111511111111 111 11 1 111 711111 3 9015 02229 1317