DEPARTMENT OF ENGINEERING RESEARCH UNI'VERSITY OF MICHIGAN UMM-3 Copy No. UNIVERSITY OF MICHIGAN Ann Arbor EXTERNAL MEMORANDUM NO. 3 PROJECT MX-794 (AAF Contract W33-038 ac-14222) Project "Wizard" "Curves for the Calculation of the Order of Magnitude of Skin Heating Due to Friction of a Missile in Steady Flight in the Atmosphere" Prepared by D. Schetzer D. W. Lueck March 10, 1947

RESTRICTED.._..... __,UNIVERSITY OF MICHIGAN CONTENTS Page Introduction.................. 1 Summary......... 2 Symbols..............***** * Use of the Design Charts...... Discussion................... 6 Future Investigations.............. 9 References...........10 Appendix............11 l l -

RE S T R I C T E D Page iii DEPARTMENT OF ENGINEERING RESEARCH Re;ort No. UMBM-...... _UNIVERSITY OF MICHIGAN LIST OF ILLUSTRATIONS Figure Title Page 1 Boundary Layer Temperature vs. Mach Number,.,.15 2 Skin Equilibrium Temperature - Supersonic Data,.16 3 Skin Equilibrium Temperature - Subsonic Data - Limit Case.......*.........17 4 Typical Missile Flight for Sample Problem,..18 5 Skin Equilibrium Temperature (Sample Problem)..19 6 Speed of Sound vs Altitude............20

REST RICTED Report No. Uld-3 1 DEPARTMENT OF ENGINEERING RESEARCH Report No. UI-3 UNIVERSITY OF MICHIGAN P 1 INTRODUCTION The importance of skin temperature on the structural design of Wizard missiles was realized in the early design stages, and work was started during the summer of 1946 to establish information concerning the feasibility of using light alloy metals. To the best of the writers' knowledge, the first investigation of this matter was made by Eber in 1939. In Reference 1 he concluded that the use of light alloy metals for the skin of the A-4.was out of the question. Experimental data on heat transfer coefficients were reported by the same author in 1941 (Keference 2), and subsequently used by Kraus and Hermann (Reference 3) to calculate the temperature of a missile in flight. Recently, several other reports have appeared on the subject of skin temperatures. Among these are the Fort Bliss report (Reference 4) which outlines a method of skin temperature calculation based on Eber's data, ana the work of G. P. Wood (Reference 5) which uses subsonic heat transfer equations given in Reference 6. Included on the Wizard program is an investigation of the strength of metals at temperatures likely to be encountered in flight. This report presents the results of skin temperature calculations based on the data of Eber, and forms a preliminary part of the skin strength investigation. It is intended to serve the dual purpose of providing the designer a means of making a rapid estimate of the order of magnitude of the skin equilibrium temperatures likely to be encountered in the high speed flight of a missile, and providing a point of departure for an experimental and theoretical study of skin heating effects. The empirical data and the methods used have been stated in the references above, and are included in the appendix of this report for the sake of completeness.

RESTRICTED DEPARTMENT OF ENGINEERING RESEARCH Rept No Page 2 ____ UNlDIVERSITY OF MICHIGAN Report No. IM-3 SUWMAKY Curves are included on Figure 2 from which a conservative estimate of the skin temperature of a missile in steady flight may be made. Similar curves based on subsonic data are given on Figure 3. These represent a conservative upper limit case. By treating accelerated flight as a succession of steady states, the maximum skin temperature of a rocket at various instances during its accelerating phase can be calculated. This has been done for the typical flight shovm on Figure 4. The results are given on Figure 5. A discussion of the factors involved in skin heating and the assumptions made in calculating temperatures are also included. The influence of temperature lag is noted and an approximation to the magnitude of this effect is given. Recommendations are made for future investigations. L,~M^~~a --- -- - -- -— M~Mi^______________________________ i, ___ _.._________ ^ _____iilii[IIIIJ

R E S T I C T E D Report No. UMM-3 DEPARTMENT OF ENGINEERING RESEARCH Pae RptIu NUNIVERSITY OF MICHIGAN rage SYMBOLS A = Surface area in sq ft a = Local speed of sound in ft per sec = Specific heat at constant pressure in Btu per lb per degree Fahrenheit cv = Specific heat at constant volume in Btu per lb per degree Fahrenheit g = Acceleration of gravity h = Average heat transfer coefficient in Btu per sec per sq ft per degree Fahrenheit h = Local heat transfer coefficient in Btu per sec per sq ft per degree Fahrenheit H = Altitude in ft = Thermal conductivity in Btu per sec per sq ft per degree Fahrenheit 2 = Characteristic length in ft M = Mach Number v a Nu = Nusselt Number h Pr = Prandtl Number Cp/g K Q = Quantity of heat in Btu Re = Reynolds Number /T = Temperature in degrees Hankine TBL - Boundary layer temperature Tamb = Ambient temperature Tskin = Skin temperature Tstag = Stagnation temperature

RESTRICTED Page 4 DEPARTMENT OF ENGINEERING RESEARCH Report o. UI - Page 4 Report No. UtIA-3 IPag 4 _____ UNIVERSITY OF MICHIGAN t = Time in sec v = Velocity in ft per sec = Ratio of specific heats P E = Emiissivity: ratio of emissive power of surface to that of black body /4 = Coefficient of viscosity in slug per ft sec = Mass density in slug per cu ft d = Stefan Boltzmann constant 17.3 x 10-1 in Btu per hr per sq ft per OR4 OF = Degrees Fahrenheit OR = Degrees Rankine

RESTRICTED H E S T R I C T E D Report No. UMM-3 DEPARTMENT OF ENGINEERING RESEARCH Pe Report No.. U..-3 lUNIVERSITY OF MICHIGAN Page 5l USE OF TME DESIGN CHARTS Figure 2 of this report may be used by the designer to estimate the order of magnitude of the skin equilibrium temperature. This is the temperature to which the skin will rise if the flight time at a given altitude and velocity is long enough for thermal equilibrium to be reached. Because a missile in powered flight is constantly accelerating, it will not remain at any given velocity and altitude long enough to reach the equilibrium value. Therefore, the actual body temperature will lag behind the value given on the chart. That is, the prediction is conservative as long as the body temperature is increasing. At some point during the ascending flight, the body temperature will reach a maximum and then start to decrease. The skin temperature will again lag behind the value given on the chart. Under these conditions, the prediction is unconservative. However, the actual temperature will not exceed the predicted maximum; for example, the peak shown on Figure 5. Temperatures computed here are for a point near the nose, - the hottest part, - of the missile. Toward the rear, the temperatures will be lower. As an approximation, in the computation of temperatures during accelerated flight, the path may be broken up into a series of steady flights. That is, over a short interval of time, the missile may be thought of as flying steadily at the average altitude for that interval. The velocities and altitudes of a missile, launched at 12~ from the vertical, during a typical flight are given in Figure 4. Suppose, for example, this flight is broken up into 2-second intervals and the temperature corresponding to the average velocity and altitude during each interval is read from Figure 2. For the interval from the 25th to the 27th second, the average velocity is found to be 4460 ft per sec and the average altitude to be 48,400 ft. Dividing the velocity by the speed of sound at 48,400 ft (from Figure 6), the Mach Number is found to be M. 4.58. The equilibrium temperature is found, from Figure 2, to be 1310 OF. Using the subsonic data of Figure 3 the temperature is found to be 1390 OF. Figure 5 shows the results of this process carried out from the time of launching to the time of burnout.

REST I CTED Page 6 l' DEPARTMENT OF ENGINEERING RESEARCH Page ~ ___...6.UNIVERSITY OF MICHIGAN Report No. UMM-5 DISCUSSION For a missile flying at high speed, the heat transfer to the skin is influenced by the heating of the boundary layer. Among the factors influencing the final temperature of the body, the following are regarded as most important: (a) Heat exchange between the boundary layer and the body. (b) Radiation from the oody to space. (c) Radiation received from the sun. (d) Transfer of heat from the skin to the interior of the missile. (e) In the case of a burning missile, heat transferred from the combustion chamber to the skin. In this analysis, only the first two factors are considered. The heat radiated by the sun to a flat plate is about 0.11 Btu per sq ft per sec when an atmosphere is not present (Reference 7). This effect is small compared to the heat exchanged between the body and the boundary layer, and is therefore neglected in this analysis. Also, the heat transferred to the interior of the missile has been ignored, because a means for its determination has not been devised. This is a subject for future study. If the missile is assumed to be in a state of steady flight under the above conditions, the skin will come to equilibrium at the temperature at which the heat radiated to space equals the heat transferred to the skin. In view of the neglect of factor (e), this analysis applies only to unfired missiles, or to that part of fired missiles which can be assumed to be insulated from combustion heat. The quantity of heat radiated to space is given by the Stefan Boltzmann Law, which shows it to be a function of the temperature and the emissivity of the surface. The radiation of heat to space tends to reduce the skin temperature. It is desirable therefore to have the emissivity as high as possible. Because the emissivity can be made very high by proper preparation of the surface, an emissivity of unity has been assumed for this study. The problem of heat transfer at high speeds between the boundary layer and the skin is not well understood. In Reference 8, the heat transfer problem for a laminar boundary layer has been treated. It has been generally assumed that the boundary layer on a body moving at supersonic speed is almost completely turbulent

R E S T R I C T E D RESTRICTED Repiort No.~ U_5 UNIVERSITY OF MICHIGANe because of the high Reynold's Numbers involved. If this assumption is true the theoretical approach holds little promise at this time. If the heat transfer coefficient (h) is dependent upon specific heat (Cp), thermal conductivity (K), velocity (v), viscosity (A'), density (f), sonic speed (a), and a characteristic length (j), it can be shown by dimensionles6 considerations that the dimensionA less combinations influencing the heat transfer process are the Nusselt Number Nu = h, the Prandtl Number Pr = P/g., the Reynolds - K - 7 Lv K Number Re a nd, and the Mach Number M = -. a Nu f(Pr, ke, M) In Reference 2, the form of this equation is determined for the case of the total heat transferred to the surface of a cone and consequently the cone angle is also involved. The dependence on cone angle is removed by basing the Reynolds Number on the free stream values downstream of the leading shock. The equation given is: Nu = 0.0107 He'82 Prandtl's Number is not involved because its variation with temperature is small. The Mach Number is involved implicitly. It is pointed out that skin temperature calculations in other reports follow the form of the equation given above, but they do not agree on the value of the coefficient. In general, calculations based on subsonic data use a value for the coefficient that is greater than 0.0107. At low speeds and altitudes where the radiation from the body is small, the influence of the coefficient is negligible. For high speeds and altitudes, its influence becomes more important. For example, at a Mach Number of six and an altitude of 100,000 ft, a change of 100% in the coefficient causes a change of 18% in the skin temperature. This point is illustrated further in the appendix. In Reference 2, Eber reports the ten Bosch relation Nu = 0.0331 Re'80 which was computed from measurements of the heat transfer to a flat plate in subsonic flow. This is taken as representative of subsonic data, and has been used as a basis of temperature calculations for an upper limit case. Results of skin temperature computations using this value of the Nusselt Number are graphed on Figure 3.

RE S T' K I CTE D Pge 8 DEPARTMENT OF ENGINEERING RESEARCH r. UNIVERSITY OF MICHIGAN? eport No. UJ The boundary layer temperature is less than the stagnation temperature because the air is not brought to rest isentropically. Experiments inaicate that, on the average, 90% of the kinetic temperature is recovered. Then, considering the specific heats of air to be constant, the temperature in the ooundary layer can be written: TBL Tamb(l + 0.9 - M2) The error introduced by considering the specific heat ratio to be a constant increases as the range between the static and stagnation values of the temperature increases. This subject is dealt with in Reference 9 where it is sho.m that at a Mach Number of six and sea level Fir the true value of Tstation is about 10% less than Tambient the value predicted oy the usual formula derived on the basis of constant K. This means that treating 6 as a constant leaas to computed boundary layer temperatures that are too high. Because of the uncertainty in the heat transfer coefficient computation, the influence of variaole specific heat is neglected. Computations taking into account the effect of molecular dissociation and variable specific heat will be undertaken in the future if more accurate data on heat transfer coefficients becomes available. At present, it is believed that for Mach Numbers less than six and moderate altitudes this effect will be small. Eber's experimental equation for the Nusselt Number has not been verified outside of the range of Reynolds Numbers between 2.5 x 105 and 1.5 x 106. The flight Reynolds Numbers based or; a fixed length for missiles flying at altitudes between sea level and 100,000 ft and at Mach Numbers between two and six, have a much greater variation than those for which Eber's data has been verified. Then, if a fixed length is used, the formula must be extrapolated. In this report Eber's data has not been extrapolated with regard to Reynolds Number. All computations are made for the Reynolds Number 1.6 x 106. It must be realized, then, in reading the graphs, that the temperature referred to is for that portion of the body lying ahead of the position for whiich Re = 1.3 x 106. For flight at constant Mach Number and varying altitude or constant altitude and varying Mach Number, this woulc mean a quite large variation in the characteristic length. For the typical flight paths now being considered for Wizard missiles, however, both altitude and Mach Number increase together. As a result, the characteristic length varies within fairly close limits.

R{ESTRICTED.R E S T R I C; T E 1) Report No. UMM-3 I DEPARTMENT OF ENGINEERING RESEARCH Page 9 UNIVERSITY OF MICHIGAN FUTURE INVESTIGATIONS 1. The flight period within the atmosphere of VWizard missiles will generally be of insufficient duration for thermal equilibrium to be reached. There are indications that the resulting temperature lag may be of real consequence in determining the maximum temperature to which the skin vail rise. An approximate calculation of the lag for the missile flight path of Figure 4 has been made for a missile having 1/16" magnesium skin. The results are drawn on Figure 5. The time necessary to reach equilibrium as a function of flight parameters and skin properties for the general case will be investigated. 2. The influence of variable specific heats and molecular dissociation will be studied. 3. For specific missiles, an attempt will be made to determine the heat loss to the interior of the missile. 4. Data is needed on the influence of Mach Number and Reynolds Number on local heat transfer coefficients for bodies of different shapes. The possibilities of utilizing;rind tunnel and flight test techniques for the determination of local heat transfer coefficients will be investigated.

RESTRICTED Page 10 DEPARTMENT OF ENGINEERING RESEARCH Rer Page 10 ___ _______UNIVERSITY OF MICHIGANReport N. U MREFERENCES 1. Eber, "Report on the Calculations of the Skin Temperature of the A-4 During Flight". WVA Archive No. 66/14. 2. Eber, "Experimentelle Untersuchung der Bremstemperature und des Warmuberganges an einfachen Kopern bei Uberschall geschwindigkeit", Peenemunde; Archive No. 66/57g. 3. Kraus-Herman, "The Magnitudes of Boundary Layer Temperatures, Heat Transfer Coefficients and Skin Temperatures of Vertically and Obliquely Launched A-4 Missiles and of the A-4b Glider". WVA Archive No. 66/167. 4. "The Calculation of the Skin Temperature of Rockets." Army Ordnance Research and Development Service, Sub-office (Rocket), Ft. Bliss, Texas. Tech. Report 17. November 1946. 5. G. P. Wrood, "Estimations of Surface Temperatures in Steady Supersonic Flight". NACA Technical Note 1114. 6. H. L. Dryden, "Aerodynamics of Cooling". Durend, "Aerodynamic Theory", Vol VI, 1934. heprint by GALCIT, Pasadena, California. 1943. 7. Croft, "Thermodynamics". McGraw-Hill Book Co., Inc., New York. 1938. 8. Karman-Tsien, "Boundary Layer in Compressible Fluids". Journal of Aeronautical Sciences, IAS, New York. April, 1938. 9. J. D. Schetzer and C. H. Lauretson, "Aerodynamic Relations with Variable Specific Heats". UMA-6, University of Michigan, Ann Arbor, Michigan. 1947. (To be released) 10. J. H. Keenan and G. Kaye, "Thermodynamic Properties of Air". John Wiley and Sons, Inc., New York. 1945.

RESTRICTED R E S T R I C T E D Report No. UMM-5 DEPARTMENT OF ENGINEERING RESEARCH Page 11 UNIVERSITY OF MICHIGAN APPENDIX Boundary layer temperature versus Mach Number is plotted for various altitudes on Figure 1, from the approximate expression for the non-isentropic retardation of air. TBL = Tamb (1 +.9 2 The values of Tam used are based upon the adopted standard atmosphere. The temperature between 35,000 ft and 100,000 ft is taken as 397~R. The influence of the temperature rise and Mach Number decrease in passing through the leading shock is neglected in the above equation for TBL. Heat Transferred Through the Boundary Layer The rate of heat transfer between the boundary layer and the skin is found from the expression =Q, hA (TBL - TsKin) Btu per sec (1) where the heat transfer coefficient is expressed by: h -KN (2) h^^ (2) Using the data of Eber, (Reference 2), this becomes: h = (0.0107) Re'82 (3a) For the limit case, the subsonic data of ten Bosch is used. This leads to a heat transfer coefficient of the form: h = - (0.0331) Re'80 (3b) The Reynolds Number is based upon free stream values downstream of the leading shock. The thermal conductivity is based upon the boundary layer temperature. After multiplying and dividing Equation 3a by {CpA}BL and rearranging terms, the heat transfer coefficient becomes: h = O.0107(oPr - jL}fe'18 (4a) lIl

RESTRICTED Page 12 DEPARTMENT OF ENGINEERING RESEARCH Report No. UMM-5 UNIVERSITY OF MICHIGAN Similarly, for the limit case, h = 0.0331 P I 20 (4b) {PrBL Re 20 Equations 4a and 4b have been simplified by setting: { L 0.4 Pr BL This represents an average value from the data in Reference 10 for boundary layer temperatures corresponding to Mach Numbers between zero and six. Furthermore, it has been assumed: /BL BL'11'V T The exponent on the temperature is actually about.76 at low temperatures and decreases as the temperature rises. At TBIJT = 6, the exponent is.68 (Reference 10). The use of the above equation introduces a small error on the unconservative side. Heat Radiated to Space The heat radiated to space is given by the Stefan Boltzmann Equation: t = 6 hAT sin Btu per sec bt 600 s where d= l7. Btu per sq ft per hr per ~R4. Setting ~ 1, the equation reduces to ~t = 4.8 ATkin Btu per sec (5) Equilibrium Under the assumptions of this analysis, the body comes to equilibrium at the temperature for which the heat radiated to space equals the heat absorbed. Thermal equilibrium is expressed by equating the values of - from Equations 1 and 5. 4.8 (TB - T (6) T~ki' h(TBL - Tsin)6 l10 sin

R E S T RI CTED Report. N DEPARTMENT OF ENGINEERING RESEARCH Report No. l..-..3.UNIVERSITY OF MIC.HIGAN 13 The solutions of Equation 6 are plotted on Figure 2 for the value of E given by Equation 4a. The solutions of 6 using h from 4b are plotted on Figure 3. Influence of Errors in the Heat Transfer Coefficient on Tk Probably the most doubtful point in the calculation of skin temperatures is the heat transfer coefficient. The values used in current reports differ by a very large percentage. The value given by Eber which is used in this report in the form h = 0.0107 (B fg. PJBL(J ReB Pr| Re'18 is regarded as a rough approximation in the present application, and though it is not possible to make a quantitative statement concerning its accuracy, it is felt that it would be unjustified to trust the formula -Within limits closer than 50%. In the calculations of Figure 2, the following approximations were used: (a) = 0.4 ( PrBL (b) /BL jBL /Lamb Tamb (c) f v upstream of shock equals fv downstream of shock. These approximations lead to errors of much smaller magnitude than the accuracy of the heat transfer coefficient formula. In the absence of radiation, the equilibrium temperature of the skin is simply equal to the temperature of the boundary layer and the heat transfer coefficient does not enter the problem. At high temperatures, Nvhere radiation is important, the skin temperature stabilizes at a value less than the boundary layer temperature. The importance of the heat transfer coefficient in the calculation of Tskin increases as the difference between TBL and Tsain increases. The decimal percent error in the skin temperature T skin can be found approximately in terms of the Tskin decimal percent error in heat transfer coefficient by differdecimal percent error in heat transfer coefficient - by differ

RESTRICTED Page 14 DEPARTMENT OF ENGINEERING RESEARCH I Report No. bUMM | I__ UNIVERSITY OF MICHIGAN erentiating Equation 6. This leads to the expression: Tskin TBL - Tskin h T4h (TBL - Tskin) + h Tskin which is used in the expression T skin h a T skin h Tskin Tskin a h h to give TBL - Tskin ATskin TbL Tskin ] Ah [ Tskin 1 TBL - T * Using Figures 1 and 2 to find the value of TBL - Tsi it is Tskin seen that at M = 6 and an altitude of 100,000 ft, the ratio is 0.61. This corresponds to a value of 0.18 for the coefficient of ~h. That is, a 50% error in h under these conditions leads to an errdr of 9% in the value of the skin temperature.

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RESTRICTED Page 18 DEPARTMENT OF ENGINEERING RESEARCH iReport No. Uli-3 UNIVERSITY OF MICHIGAN 100 000 60000 tL. 400001111111 I —. 20 000 ii_ _ _ _ _ _ _ I I II 1 1111 1 II I I II II.I I I {11 01111 BHH-{I~ifilil fllil 414~111 F T 111+11 O 2000 4000 6000 8000 VELOCITYr,-V CFT./SEC.) Figure 4 TYPICAL i'~SSILE FLIGHT FOR SAMPLE PROBLEM S oo 1 I X WS W MMgITY, Vt CFT111111SEC 11111, t ##W#H 41110Fi1ire; rtT r 1 11 __ _ l TYPI I C I I 1 XIX " M SI L E 1111 F IGHTXrr11111 fXlT XXW||

RESTRICTED Report No. UMM-3 DEPARTMENT OF ENGINEERING RESEARCH Page 19 UNIVERSITY OF MICHIGAN 3000 i. BOUNDARY LAYER TEMP&RA'TURE I: I I 2. SIm EQUILIBRIUM TEMPERATURE I1 I 2800 ($UBWONIC DATA) L: 3.,SIN EOUILlORIUM TEMPERATURE (SUPERSONIC DATA) 1l | 2600 4. TRANSIENT SKIN TEMPERATURE t! 1t6IeMAGNESIUM SKIN (SUPERSONIC DATA): f 2200 1800 Il lllll lllllllllll II 1 120 II _ Il l l iil li Il. I l ^ ^ __. WLiiiiiiiililiiiiil*ii ili i iiiiiiiiil 00 — 4 e i r 19 20 2_ 2B -2 s_ _ E I$$ _ $ _ | it I I _ _I n ~ llTlMEf -t SECwl Figure 5 1400 I I IT Vil I; [_, __1 _ _ _ _ _ __ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ -1 1 _ _ _. _. _ _ _ _ _ _ _ _ _ _ _ _ _~~~~~~~~~~If ilfil

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UNIVERSITY OF MICHIGAN DISTRIBUTION LIST A-1 Guided Missiles Committee A-50 Chief, Guided Missile Branch Joint Research & Development Technical Command Board Edgewood Arsenal, Maryland New War Department Building Washington, D. C. A-51 Commanding General Aberdeen Proving Ground, Md. A-2 Commanding General Attention: Ballistic Rethru Army Air Forces search Laboratory A-7 Washington 25, D. C. Attentions AC/AS-4, DRE-3, A-52 Commanding General Pentagon Proving Ground Command Eglin Field, Florida A-8 Commanding General Attention: First Experimenta thru Air Materiel Command Guided Missiles A-32 Wright Field, Dayton, Ohio Group Attention: TSEON-2 A-53 Commanding Officer A-33 Commanding General Antiaircraft Artillery School Air University Fort Bliss, Texas Maxwell Field, Alabama Attention: Air University A-54 Commanding Officer Library Frankford Arsenal Philadelphia 37, Pennsylvania A-54 Chief of the Bureau of Attention: Fire Control thru Aeronautics Design Division A-39 Navy Department Washington 25, D. C. A-55 Commanding Officer Attention: TD-4 Naval Air Materiel Center Philadelphia, Pennsylvania A-40 Chief of the Bureau of thru Ordnance A-56 Commanding Officer A-43 Navy Department Naval Aircraft Modification Washington 25, D. C. Unit Attention: Re-9 Johnsville, Pennsylvania A-44 Chief of the Bureau of Ships A-57 Commanding Officer thru Navy Department thru Signal Corps Engineering A-46 Washington 25, D. C. A-58 Laboratories Attention: Code 343 Bradley Beach, New Jersey A-47 Chief of Chemical Corps A-59 Commanding Officer Room 4E589 - Pentagon U. 3. Naval Air Missile Washington 25, D. C. Test Center Point Mugu, California A-48 Chief of Naval Research thru Navy Department A-60 Commanding Officer A-49 W.'ashington 25, D. C. U. S. Naval Ordnance Test Attention: Technical Inform- Station ation Section Inyokern, California

DEPARTMENT OF ENGINEERING RESEARCH UNIVERSITY OF MICHIGAN A-61 Comma nding Officer A-76 Officer-in-Charge Tendover Army Air Field Research & Development.fenaover, Utah Service Suboffice (Rocket) Fort Bliss, Texas A-62 Director, David Taylor Model Basin A-77 Watson Laboratories.Jashington, D. C. Air Materiel Commend Attention: Aero Mechanics Eatontown, New Jersey Division A-78 Istson Laboratories, AMC A-63 Director, National Advisory Cambridge Field Station thru Committee for Aeronautics 250 Albany Street A-66 1500 New Hampshire Avenue, N. W. Cambridge 39, Massachusetts Washington, D. C. Attention: Mr. C. H. Helms A-79 The Library Joint Research & Development A-67 Director, Naval Research Board thru Laboratory New War Department Building A-69 Anacostia Station Washington 25, D. C. Washington, D. C. A-70 Director, Special Devices Center C-5 bell Telephone Laboratories Office of Naval Research Murray Hill, New Jersey Sands Point Attention: Dr. W. A. MacNair Port Washington, L. I. New York Attention: Technical Information C-6 Bendix Aviation Corporation Desk Special Products Development, East A-71 First Antiaircraft Artillery Teterboro, New Jersey Guided Missiles Bn. Attention: Dr. Harner SelV hite Sands Proving Grounds vidge Los Cruces, New Mexico C-7 Boeing Aircraft Corporation A-72 Head of Postgraduate School Seattle 14, Washington U. S. Naval Academy Attention: Mr. R. H. Nelson Annapolis, Maryland C-12 Curtiss-Wright Corporation A-73 Office of the Chief of Ordnance Columbus 16, Ohio Research & Development Service Attention: Mr. K. Darby Rocket Development Division Pentagon C-14 Douglas Aircraft Company Tashington 25, D. C. thru 3000 Ocean Boulevard C-15 Santa Monica, California A-74 Officer-in-Charge Attn: Mr. A. E. Raymond Bureau of Ordnance Experimental Mr. E. F. Burton Unit Hydraulics Building C-19 General Electric Company National Bureau of Standards Project Hermes;ashington 25, D. C. Schenectady, New York Attention: Dr. C. K. Bauer A-75 Officer-in-Charge Naval Ordnance Laboratory Naval Gun Factory!e shington 25, D. C.

DEPARTMENT OF ENGINEERING RESEARCH 3 UNIVERSITY OF MICHIGAN C-21 General Electric Company Aviation Division Schenectady, New York Attention: Mr. S. A. Schuler,Jr. Mr. Phillip Class C-23 Glenn L. Martin Company Baltimore 3, Maryland Attention: Mr. V. B. Bergen C-26 Goodyear Aircraft Plant "B" Akron 17, Ohio Attention: Mr. A. J. Peterson C-33 M. W. Kellogg Company Foot of Danforth Avenue Jersey City 3, N. J. Attention: Dr. G. H. Messerly C-38 Northrop Aircraft Inc. Hawthorne, California C-43 Radio CorporatoluD f America Victor Division Camden, New Jersey Attention: Mr. T. T. Eaton C-44 Radioplane Corporation Metropolitan Airport Van Nuys, California C-46 Republic Aviation Corporation Military Contract Dept. Farmingdale, L.I., N.Y. Attention: Dr. William O'Donnell C-47 Ryan Aeronautical Company Lindberg Field San Diego 12, California Attention: Mr. 3. T. Salmon

DEPARTMENT OF ENGINEERING RESEARCH 4 I DEAMUNIVERSITY OF MICHIGAN CONTRACTOR TRANSMITTED VIA C-1 Applied Physics Laboratory Development Contract Officer thru Johns Hopkins University Applied Physics Laboratory C-5 Silver Spring, Maryland Johns Hopkins University Attention: Dr. Dwight E. Gray 8621 Georgia Avenue Silver Spring, Maryland C-4 Bell Aircraft Corporation Bureau of Aeronautics Rep. Niagara Falls, New York Cornell Aeronautical Lab. Attention: Mr. R. H. Stanley Box 56 Mr. B. Hamlin Buffalo, New York C-8 Consolidated-Vultee Aircraft Development Contract Officer Corporation Consolidated-Vultee Aircraft Corp. Lone Star Laboratory Daingerfield, Texas Daingerfield, Texas Attention: Mr. J. E. Arnold C-9 Consolidated-Vultee Aircraft Representative-in-Charge, BuAer Corporation Consolidated-Vultee Aircraft Corp. Dovmey, California Vultee Field Attention: Mr. W. M. Robinson Downey, California C-10 Cornell Aeronautical Lab. Development Contract Officer Buffalo, New York Cornell Aeronautical Lab. Attention: Mr. W. M. Duke Buffalo, New York C-ll Curtiss-Tright Corporation Bureau of Aeronautics Rep. Columbus, Ohio Curtiss-Wright Corporation Attention: Mr. Bruce Eaton Columbus 16, Ohio C-13 Douglas Aircraft Co. Bureau of Aeronautics Rep. El Segundo Branch Douglas Aircraft Co. El Segundo, California El Segundo, California Attention: Mr. E. H. Heinemann C-16 Eastman Kodak Company Naval Inspector of Ordnance Navy Ordnance Division Navy Ordnance Division Rochester, New York Eastman Kodak Company Attention: Dr. Herbert Trotter 50 West Main Street Rochester 4, New York C-17 Fairchild Engine & Airplane Representative-in-Charge Corporation Fairchild Engine & Airplane Corp. Pilotless Plane Division Pilotless Plane Division Farmingdale, Long Island, N.I. Farmingdale, Long Island, N. Y. Attention: Mr. J. A. Sloan C-18 The Franklin Institute Commanding Officer Laboratories for Research and Naval Aircraft Modification Unit Development Johnsville, Pennsylvania Philadelphia, Pa. Attention: Mr. R. H. McClarren

DEPARTMENT OF ENGINEERING RESEARCH 5 UNIVERSITY OF MICHIGAN CONTRACTOR TRANSMITTED VIA C-20 General Electric Company Development Contract Officer Federal & Marine General Electric Co. Commercial Division Schenectady, New York Schenectady, New York Attention: J. W. Frick C-22 Glenn L. Martin Company Bureau of Aeronautics Rep. Baltimore, Maryland Glenn L. Martin Co. Attention: Mr. W. K. Ebel Baltimore 5, Maryland C-24 Globe Corporation Inspector of Naval Materiel Aircraft Division 141 W. Jackson Blvd. Joliet, Illinois Chicago 4, Illinois Attention: Mr. J. A. lTeagle C-25 Goodyear Aircraft Corp. Bureau of Aeronautics Rep. Akron, Ohio Goodyear Aircraft Corp. Attention: Dr. Carl Arnstein Akron 15, Ohio C-27 Grumman Aircraft Bureau of Aeronautics Rep. Engineering Corporation Grumman Aircraft Engr. Corp. Bethpage, Long Island, N.Y. Bethpage, L.I., N. Y. Attention: Mr. William T. Schwendler C-28 Hughes Aircraft Company Bureau of Aeronautics Rep. Culver City, California Douglas Aircraft Co. Attention: Mr. R. E. Hopper El Segundo, California Mr. D. H. Evans C-29 Jet Propulsion Laboratory Officer-in-Charge thru California Institute of Research & Development Service C-30 Technology Suboffice (Rocket) California Institute of Technology Pasadena 4, California C-31 Kaiser Fleetwings, Inc. Bureau of Aeronautics Rep. Bristol, Pennsylvania De Laval Steam Turbine Co. Attention: Mr. Carl DeGanahl Trenton, N. J. C-52 Kellex Corporation Inspector of Naval Materiel New York, New York 90 Church Street New York 7, N. Y. C-34 Chairman, MITGMC Navy Ordnance Resident thru Project Meteor Office Technical Liaison Officer C-35 Massachusetts Institute of Massachusetts Institute of Technology Technology Cambridge, Mass. Room 20-C-135 Attention: Dr. H. G. Stever Cambridge 39, Mass.

DEPARTMENT OF ENGINEERING RESEARCH. 6. UNIVERSITY OF MICHIGAN CONTRACTOR TRANSMITTED VIA C-56 McDonnell Aircraft Corp. Bureau of Aeronautics Rep. St. Louis, Missouri McDonnell Aircraft Corp. Attention: Mr. W. P. Montgomery P. 0. Box 516 St. Louis 21, Missouri C-37 North American Aviation Inc. Bureau of Aeronautics Resident Rep. Los Angeles, California Municipal Airport Attention: Dr. Wm. Bollay Los Angeles 45, Calif. C-39 Princeton University Development Contract Officer Physics Department Princeton University Princeton, New Jersey Princeton, New Jersey Attention: Dr. John A. Wheeler C-40 Princeton University Commanding Officer thru Princeton, New Jersey Branch Office C-42 Attention: Project SQUID Office of Naval Research 90 Church Street - Rm 1116 New York 7, New York C-45 Ratheon Manufacturing Co. Inspector of Naval Materiel "Waltham, Massachusetts Park Square Building Attention: Mr. R. C. Saunders Boston 16, Mass. C-48 S. W. Marshall Company Inspector of Naval Materiel Shoreham Building 401 Water Street Washington, D. C. Baltimore 2, Maryland C-49 Sperry Gyroscope Co., Inc. Inspector of Naval Materiel Great Neck, L.I., N. Y. 90 Church Street New York 7, N.Y. C-50 United Aircraft Corp. Bureau of Aeronautics Rep. Chance Vought Aircraft Div. United Aircraft Corp. Stratford, Conn. Chance Vought Aircraft Div. Attention: Mr. P. S. Baker Stratford 1, Conn. C-51 United Aircraft Corp. Bureau of Aeronautics Rep. Research Department United Aircraft Corp. East Hartford, Conn. Pratt & Whitney Aircraft Div. Attention: Mr. John G. Lee East Hartford 8, Conn. C-53 University of Texas Development Contract Officer Defense Research Lab. 500 East 24th Street Austin, Texas Austin 12, Texas Attention: Dr. C. P. Boner C-54. Willys-Overland Motors, Inc. Representative-in-Oharge BuAer Maywood, California Consolidated-Vultee Aircraft Corp. Attention: Mr. Joe Talley Downey, Calif.

DEPARTMENT OF ENGINEERING RESEARCH UNIVERSITY OF MICHIGAN 7. CONTRACTOR TRANSMITTED VIA DA-1 New Mexico School of Mines Development Contract Officer Research & Development Div. New Mexico School of Mines Albuquerque, New Mexico Albuquerque, New Mexico DA-2 New Mexico School of Agri- Development Contract Officer culture & Mechanic Arts New Mexico School of Mines State College, New Mexico Albuquerque, New Mexico Attention: Dr. Gardner Development Contract Officer DA-3 New York University Inspector of Naval Materiel Applied Mathematics Center 90 Church Street New York, New York New York 7, New York Attention: Mr. Richard Courant DA-4 Office of the Chief of Ordnance Research & Development Service Research & Materials Division Ballistics Branch The Pentagon \Washington 25, D. C. DA-5 Polytechnic Institute of Brooklyn Inspector of Naval Materiel Brooklyn, New York 90 Church Street Attention: Mr. R. P. Harrington New York 7, New York DA-6 University of Minnesota Inspector of Naval Materiel Minneapolis, Minnesota Northern Pump Co. Attention: Dr. Akerman Minneapolia, Minn.

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