ENGINEERING RESEARCH INSTITUTE THE UNIVERSITY OF MICHIGAN ANN ARBOR Quarterly Report ATMOSPHERIC PHENOMENA AT HIGH ALTITUDES (November 1, 1957 to January 31, 1958).) F. L\Bartman V. C. Liu E. A. Wenzel Approved: L. M. Jones Department of Aeronautical Engineering ERI Project 2387 DEPARTMENT OF THE ARMY PROJECT NO. 3-17-02-001 METEOROLOGICAL BRANCH, SIGNAL CORPS PROJECT NO. 1052A CONTRACT NO. DA-36-039 SC-64659 April 1958

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The University of Michigan * Engineering Research Institute TABLE OF CONTENTS Page LIST OF FIGURES AND TABLES iv ABSTRACT v THE UNIVERSITY OF MICHIGAN PROJECT PERSONNEL vi 1. INTRODUCTION 1 2. GRENADE EXPERIMENT 1 2. 1 Aerobee Firings at Ft. Churchill 1 2. 2 Data Reduction 5 2. 3 Comparison of SM1. 01 DOVAP Data with SM1. 01 7 Ballistic Camera Data 3. AI.R - SAMPLING EXPERIMENT 11 3.1 Scope of the Work 11 3.2 Analysis of Contents of Blank Bottles 11 3.3 Bottle Leak Testing 13 4. THEORETICAL WORK ON DIFFUSIVE SEPARATION OF GAS MIXTURES IN FLOW FIELDS 14 5. LECTURES BY PROFESSOR SYDNEY CHAPMAN 17 6. LABORATORIES VISITED 21 7. ACKNOWLEDGEMENTS 21 iii

The University of Michigan * Engineering Research Institute LIST OF FIGURES AND TABLES Figures No. Page 1. Launching of Aerobee SM2. 10, Carrying Both "Grenade" 4 and "Falling Sphere" Experiments. 2. Comparison of the University of Michigan (Paneth) and 15 the Russian Sampling Results. Tables I Schedule of Operations for Aerobees. 1 II University of Michigan - SEL. Gre-ade Aerobees at Ft. Churchill. III Grenade Aerobee Position Data from Third DOVAP Data 6 Reduction on SM1. 01. IV Estimated Position of Grenade Bursts Relative to DOVAP 8 Antenna System on SM1. 01. V Comparison of DOVAP and Ballistic Camera Grenade 9 Burst Position Data for SM1. 01. VI Comparison of DOVAP and Ballistic Camera Layer Data 10 for SM1.01. VII Control Checks on Sample Bottles. 12 VIII Helium Leak Checks on Various Bottles. 13

The University of Michigan * Engineering Research Institute ABSTRACT Four grenade Aerobees were fired at Ft. Churchill in December, 1957, and January, 1958. Two of these were fired at midnight and noon of the same day to yield a measurement of diurnal variations. SM2. 10 carried both the "Grenade" and "falling sphere" experirents for comparison of results. Data reduction of SM1.01 has been finished; cycle counting on SM1.02 has been finished; "spin corrections" are now being made. Control checks were run on various air sample bottles. The results of these checks are given. University of Michigan sampling results (Argon ratio) are compared with some Russian results reported recently. Two papers on diffusive separation of gas mixtures in flow fields by V. C. Liu have been accepted for publication: "A Note on Diffusive Separation of Gas Mixtures in Flow Fields", (Journal of Applied Physics), "On the Separation of Gas Mixtures by Suction of the Thermal-Diffusion Boundary Layer", (Quarterly Journal of Mechanics and Applied Mathematics, Oxford). A series of lectures on geophysics and solar physics was given by Professor Sydney Chapman. I - v

The University of Michigan * Engineering Research institute THE UNIVERSITY OF MICHIGAN PROJECT PERSONNEL Both Part Time and Full Time Allen, Harold F., Ph.D., Research Engineer Bartman, Frederick L., M. S., Research Engineer Billmeier, William G., Assistant in Research Harrison, Lillian M., Secretary Henry, Harold F., Electronic Technician Jew, Howard, M. A., Research Assistant Jones, Leslie M., B.S., Project Supervisor Kakli, G. Murtaza, B.A., Assistant in Research Kakli, M. Sulaiman, M.S., Assistant in Research Liu, Vi-Cheng, Ph.D., Research Engineer Loh, Leslie T., M. S., Research Associate Nelson, Wilbur C., M.S. E., Prof. of Aero. Eng. Otterman, Joseph, Ph.D., Research Associate Schumacher, Robert E., B.S., Assistant in Research Stohrer, Albert W., B.S., Research Associate Taylor, Robert N., Assistant in Research Titus, Paul A., B.S., Research Associate Wenzel, Elton A., Research Associate Whybra, Melvin G., M.A., Technician Wilkie, Wallace J., M.S.E., Research Engineer Zeeb, Marvin B., Research Technician vi

The University of Michigan * Engineering Research Institute 1. INTRODUCTION This is the eleventh in a series of quarterly reports on Contract No. DA-36-039 SC-64659. The purposes of the contract are: a. to adapt the rocket grenade experiment for use in the Artic during the International Geophysical Year; b. to participate in the preparation and firing of the IGY rocket grenade experiments; c. to collect and analyze upper-air samples; and d. to engage in the general investigation of problems relating to upper-air research. 2. GRENADE EXPERIMENT 2. 1 AEROBEE FIRINGS AT FT. CHURCHILL IGY Grenade Aerobee rockets SM1. 07, SM1.08, SM1. 09 and SM2. 10 were fired at Ft. Churchill on December 11 and 14, 1957, and on January 27, 1958. The schedule of operations at Ft. Churchill is given in Table I. TABLE I SCHEDULE OF OPERATIONS FOR AEROBEES SM1.07, SM1.08, SM1.09 ANDSM2.10 SM1.07 SM1.08 SM1.09 SM2. 10........, ~,,-., - -, - - -. - - -, _,, - Horizontal Test Dec. 6, 1957 Dec. 5, 1957 Jan. 23, 1958 Jan.23,1958 Vertical Test Dec.ll, 1957 Dec.13,1957 Jan. 26, 1958 Jan.27,1958 Firing 2159:45 CST 1500:10 CST 0004:25 CST 1248:34 CST Dec. 11, 1957 Dec.14, 1957 Jan.27, 1958 Jan.27,1958 1

-- ro TABLE II UNIVERSITY OF MICHIGAN-SEL GRENADE AEROBEES AT FT. CHURCHILL B. 0. B.O. B.O. Peak Flight C Hour Date Time Vel. Alt. Time No.. CST sec ft/sec 103 ft sec Peak Grenades Altitude Alt. not Arrivals Range of I miles Exploded Recorded Experiment C no. km I~~~~~~~~~~~~~~ I_ i SM 1. o1 0551 11/12/56 (Night) 1.02 2216 7/21/57 (Twilight) 1.03 2330.7/23/57 (Twilight) 1.04 1000 8/12/57 (Day) 1.05 2030 8/19/57 (Twilight) 2.06 0808 8/25/57 (Day) 1.07 2159 12/11/57 (Night) 1.08 1500 12/14/57 (Day) 1.09 0004 1/27/58 (Night) 2.10 1248 1/27/58 (Day) 36 36 35 33 36 44 44 36 33 3250 4110 4050 3500 4000 4800 3500 4100 4250 64 136 77 158 68 151 61 140 73 95 80-85 77 71 92.5 157 200 154-159 158 161 203 42 58 55 46 58 85 50-53 58-60 59 90 8,18 1-7 25-60 9-17 14 1-18 26-87 9 1-8 25-82 10-19 1,7 2-6 22-70 8-19 14 1-13 26-76 15-16 16 1-13 30-90 1 2-19 24-82 1-15 26-72 6 1-5 26-90 7-19 4.16 1-3 30-A90 x x x x x x x x x x - -- C' Supporting < Balis. Met.;amera Data. _t. x x x x m:t -I x 3 X x x -I Q x y X w *. X''."" 43.5 5000 5-15 17-18

t The University of -Michigan Engineering Research Institute 1 Aerobee SM1.07 performance was below normal. The estimated peak altitude for this flight is 48 miles (radar-tabulated data) instead of the prey dicted 58 miles. Maximum'velocity was 3750 ft/sec instead of the predicted 4100 ft/sec and burnout time was 44. 8 seconds instead of the predicted 33 seconds. Although rocket performance was not monitored, it is suspected that the regulator did not function properlyo The performance of the other three rockets was excellent; indeed, SM2. 10 with peak altitude of about 90 miles seems to have exceeded it's expected performance. All of the grenade experiments on these rockets were successfulo The percentage of grenades not detonated was about the same as on previous flights: grenade number 1 on SM1.07, grenade number 6 on SMlo 09, grenades number 4 and 16 on SM2. 10. All grenades were detonated successfully on SM1. 08. Sound ranging, ground flash detector, and DOVAP records were excellent for all flights. It appears that the arrival from the last grenade on SM2. 10 was obtained successfully. It is estimated that this grenade may have been exploded as high as 92 km. Each of the Aerobees SM1.07 and SM1.08 carried two grenades mad of a high-explosive mixture not containing aluminum powder. This was done in an attempt to obtain some additional information on the nature of the mechanism of the explosion-induced modulation of the DOVAP cycle-count record. Three of these four grenades were detonated successfully. A pre~ liminary examination of the modulation did not reveal any effect different from that previously obtained. SM1.09 and SM2. 10 each carried one l-lb grenadeo On SMlo09 this grenade was exploded at about 45 km, on SM2. 10, at about 65 km. Sound arrivals were recorded successfully for each of these explosionso It is possible that on future experiments l-lb grenades could be used to altitudes up to 70 or 75 km. The payload weight of the grenade experiment rockets could be reduced considerably over the present design. SM1. 09 and SM2. 10 were flown at approximately midnight and noon respectively of the same day. Thus the data from these two rockets will yield a measurement of diurnal upper-air-temperature variationso Figure 1 shows the launching of SM2. 10. SM2. 10 contained both the grenade experiment for upper-air -temperature and winds and the sphere experiment for upper-air density. The comparison of data from the two experiments will give valuable information regarding, I 3 -

The University of Michigan e Engineering Research Institute I. Fig. 1, Launching of Aerobee SM2. 10, Gar'rying Both "Grenade" and "Falling-Sphere" Experiment".',, and Falling S e~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~

[ The University of Michigan Engineering Research Institute their accuracy. A third comparison will be possible from the results of Niki-Cajun AM6. 36. This rocket carried alphat-ron gauges for the determination of upper-air pressure, density, and temperature by means of the measurement of imact and cone-wall pressures. This rocket was flown about 30 minutes after SM2. 10. These firings completed the series of IGY series of Grenade Aerobee rockets. Table II is a summary of the performance of the ten rockets in these series. Each experiment was flown successfully. 2.;: DATA REDUCTION The third and final calculation of SM1. 01 DOVAP data was completed, The position at half-second intervals with respect to the Aerobee launcher was computed up to 148 seconds. Position-vs. -time data are given as follow s a) at 0.5-second intervals from 1-100 seconds, and from 129.5 —148 seconds. b) at 5-second intervals from 100-129o5 seconds. Peak time has been determined as 132.0 seconds, peak altitude at 223, 886 feet (42 41 miles, 68.24km). Grenade-position data were computed with respect:r. the Aerobee launcher, and with respect to the center microphone at Tw:i] Lakes, The grenade-explosion coordinate data and the layers between grenades, referred to the center microphone at Twin Lakes, are given in Table III. Standard deviations are also given. This data reduction appears to give very good results, using the criterion for results outlined by Wo Dean at one of the past SGIGY meetings, i.e., for Ft. Churchill JDOVAP data reduction, Ocu = 5 feet -"good" (normal) -U = 8 feet -"probably Oo Ko" - = 15 feet - "something wrong". Taking the data from Table II for grenades 3 and 10 at altitudes of 20 and 30 miles, respectively, we have: Grenade 3 3 ft. 3 fto 3 ft. 1-1 5 ft. Grenade 10 2 ft. 2 ft. 2 ft. 1 ft. where ratios Ofw~e ~ w-re re taken from graphs prepared by W. Dean for the Ft. Churchill range.

The University of Michigan Engineering Research Institute TABLE III GRENADE AEROBEE POSITION DATA FROM THIRD DOVAP DATA REDUCTION ON SM1,01* Grenade No. Range Time X(+N) T y(+w) Ir z(msl) z I 1 2-1 2 3-2 3 4-3 4 5-4 5 6-5 6 7-6 7 9-7 9 10-9 10 11-10 11 12-11 12 13-12 13 14-13 14 15-14 15 16-15 16 17-16 17.. sec ft 41.774 25332.78 -2455.05 45.204 22877.73 -2426.95 48.663 20450.78 -2454.30 52.188 17996.48 -2412.56 55.650 15583.92 -2368.65 59.080 13215.27 -2398.69 62.560 10816.58 -4793.70 69.527 6022.87 -2349.36 72.945 3673.51 -2407.02 76.462 1266.49 -2391.66 79.955 -1125.17 -2335.87 83.371 -3461.04 -2385.91 86.873 -5846.95 -2385.62 90.373 -8232.57 -2352.81 93.837 -10585.38 -2375.56 97.350 -12960.94 ft 6.69 4.23 2.46 0.38 2.85 1.75 1.09 1.87 2.97 1.99 0.98 1.12 0.14 3. 18 3.32 1.22 2.11 1.28 3.38 0.60 2.78 0.84 1.95 1.02 2.96 0.87 2.09 1.32 0.77 3.09 3.85 ft 7103.35 1110.86 8214.21 1104.08 9318.29 1116.51 10434.79 1089.60 11524.39 1076.61 12601.00 1093.70 13694.69 2188.06 15882.75 1080.05 16962.80 1105.51 18068.31 1100.41 19168.72 1079.42 20248, 14 1098.92 21347.05 1108.41 22455.46 1084.73 23540.19 1102.62 24642.81 ft 7.29 4.61 2.68 0.42 3. 10 1.91 1.18 2.05 3.23 2, 18 1.05 1.22 0. 17 3,48 3.64 1.33 2.32 1.38 3.70 0 64 3.05 0.91 2.14 1.11 3.25 0.95 2.30 1.44 0.86 3.38 4,24 ft 82607.41 10489. 17 93096.58 9992.03 103088.61 9720.50 112809.10 9117.35 121926.45 8626. 68 130553. 13 8348.99 138902. 12 15521.14 154423.26 7037. 67 161460.93 6847.48 168308.40 6403.07 174711.47 5880.60 180592.07 5636.82 186228.89 5237. 76 191466.65 4793.72 196260.37 4467. 37 200727.74 ft 1. 14 0.74 0.41 0.08 0.47 0.29 0. 18 0. 32 0.49 0. 33 0. 16 0. 19 0 03 0.60 0.63 0.21 0.41 0.26 0.68 0. 10 0.58 0. 16 0.42 0.23 0. 64 0. 17 0.47 0. 29 0. 18 0.73 0.91 * Referred to a right cartesian coordinate system having its origin at sea level at the center microphone at Twin Lakes and having its x-y plane tangent to Clark Spheroid at that point. 6

The University of Michigan * Engineering Research Institute The data reduction on SM1. 02 is coming along very well. The initial cycle counting of all eight channels (each by two different persons) has been completed. The "spin" corrections are now being made, 2. 3 COMPARISON OF SM1.0 1 DOVAP DATA WITH SMl1 01 BALLISTIC CAMERA DATA The Ballistic Camera data reduction for Aerobee SMIo 01 has been completed. The results are contained in a technical note issued by BRL. 1 The comparison of the DOVAP and Ballistic Camera data for SM1. 01 grenade bursts is very interesting. The DOVAP position data refers to the position of a point on the longitudinal axis of the missile corresponding to the center-line of the DOVAP missile antenna system. However the grenades are exploded at a point forward of the nose cone. The DOVAP data must be corrected for this difference of position before they are compared with the Ballistic Camera coordinates of the grenade burstso Although the grenades were designed to be detonated when the lanyarc was fully unwound, movies of ground test firings of the grenades show that the grenades do not always travel to a distance corresponding to a complete unwinding of the lanyard before exploding. DOVAP telemetry on SMlo 01 confirms this fact for the grenade explosions on SM1.01o The time interval between actual ejection, monitored by a microswitch, and the actual explosion, monitored by a missile-borne flash detector, varies from grenade to grenade. Assuming that the ejection velocity is the same for each grenade and that the maximum time interval corresponds to a full unwinding of the lanyard, the relative distance between the DOVAP antenna system centerline and the explosion can be computed approximately. An additional complication arises from the fact that the missile is probably precessing, and so the vector representing the relative position is also precessing in space. On SMlo01l, the correction was made under the assumption that the correction vector was in the direction of the tangent to 1. Laura Ewalt, "Photogrammetrically Determined Spatial Coordinates for Aerobee SM1.01 Grenade Bursts During IGY Firings at Fort Churchill, Canada", BRL, TN 1157, December 1957.

1 The University of Michigan * Engineering Research Institute TABLE IV ESTIMATED POSITION OF GRENADE BURSTS RELATIVE TO DOVAP ANTENNA SYSTEM ON SM1. 01 Grenade No. 1 2 3 4 5 6 7 9 10 11 12 13 14 15 16 17: <x (+N) -4.02 -4. 76 -4.46 -5.83 -6.03 6. 12 -6.48 -6. 35 -6.24 7. 76 7. 72 5. 17 -8.60 -9. 76 -7.49 -10.59 6y(+N) 1.80 2. 12 1.99 2.60 2. 74 2.73 2.89 2.86 2.83 3.57 3.61 2.36 4.00 4.49 3.45 4.88 6 z(+up) 17. 35 19. 83 17. 84 22.41 22. 34 21.69 21.77 19.91 18.05 21.25 20. 06 12.57 19.52 20.56 14, 52 18.77 I 8

. TABLE V COMPARISON OF DOVAP AND BALLISTIC CAMERA GRENADE-BURST-POSITION DATA FOR SM1.01* x(+N) y(+W) z(MSL) -— 4 m~ 9 r. Ax.. Ay DOVAP BC DOV-BC DOVAP BC DOV-BC DOVAP BC' DO 1 -17211.23 -17276.87 65.64 5647.95 5711.93:863.98 82754.69 82726,21 28 2 -19688.36 -19757.18 68.82 6758.11 6830.69 -72.58 93241.61 93231.44 10 3 -22135.36 -22211.24 75.88 7861.09 7939.62 -78.53 103226.60 103211.73 14 4 -24609.82 -24691.55 81.73 8977.26 9061.66:-84.40 112946.76 112926.28 20 5 -27042.15 -27119.37 77.22 10066.09 10160.74 -94.63 122059.21 122040.44 18 6 -29428.46 -29514.38 85.92 11141.82 11240.13 -98.31 130680.51 130672.31 E 7 -31844.53 -31945.47 100.94 12234.83 12332.65 -97.82 139024.77 139012.19 12 9 -36669.75 36787.98 118.23 14421.24 14524.25 -103.01 154534.47 154543.65 - 10 -39033.35 -39146.90 113.55 15500.50 15600.36 -99.86 161565.59 161571.20 -5 11 -41455.88 -41581.28 125.40 16606.00 16715085 -109.85 168411.46 168421.58 -10 12 -43860.59 -43979.57 118.98 17705.74 17808.36 -102.62 174808.55 174815.92 -7 13 -46205.92 -46331.93 126.01 18783.22 18897.60 -114.38 180677.01 180668.93 E 14 -48606.7/ -48730.22 123.44 19883.12 20006.52 -123.40 186316.01 186289.00 27 15 -51004.29 -51141.63 137.34 20991.38 21108.88 117.50 191550.05 19-1525.21 24 16 -53364.64 -53497.27 132.63 22074.48 22198.12 -123.64 196333.04 196288.98 44 17 -55752.47 -55895.56 143.09 23177.94 23307.04 -129.10 200799.91 200777.1' 22 *With reference to a right cartesian coordinate system having its origin at sea level at the Aerobee launcher and its x-y plane tangent to the Clark spheroid at that point. AZ. V-BC rD -I 3.48 ).17 o 1.87. 48 3.77 s 3.20. 68 O. 18;.61 ).12 m 7.37 3 08 3 7.01 m c.84 3 1. 06;.75 0) Yb Yr I

TABLE VI COMPARISON OF DOVAP AND BALLISTIC CAMERA DATA FOR LAYERS x (+N) y(+W) BETWEEN GRENADES ON SM1o01:r mo z(MSI 1 2 3 4 5 6 7 o 9 10 11 12 13 14 15 16 17 DOVAP -2477. 13 -2447. 00 -2474.46 -2432.33 -2386.31 -2416.07 -4825.22 -2363.60 -2422.53 -2404.71 -2345.33 -2400.86 -2397.51 -2360.35 -2387.83 BC -2480.31 -2454.06 -2480.31 -2427.82.2395. 01 -2431,09 -4842051 -2358.92 -2434.38 -2398 29 -2352. 36 -2398.29 -2411.41 -2355.64 -2398.29 Ax DOVB C DOVAP 3.18 1111. 16 7. 06 1102.98 5.85 1116.17 -5.51 1088.83 8.70 1075.73 15.02 1093.01 17.29 2186.41 -4.68 1079.26 11.85 1105.50 -643 1099.74 7 03 1077.48 -2.57 1099.90 13.90 1108.26 4. 471 1083. 10 10.46 1103.46 Ay BC DOV-BC DOVAP BC 1118.76 1108.93 1122. 04 1099.08 1079. 39 1092.52 2191.60 1076.11 1115.49 1092. 51 1089.24 1108.92 1102. 36 1089.24 1108. 92 -7. 60 -5.95.5. 87 -10.25 -3. 66 0.49 -5.19 3.15 -9.99 7.23 -11.76 0.98 5090 6,0 14 -50 46 10486.92 9984.99 9720. 16 9112.45 8621.30 8344 26 15509.70 7031.12 6845.87 6397.09 5868.46 5639.00 5234. 04 4782.99 4466.87 10505. 9980. 9714. 9114. 8631. 8339. 15531. 7027. 6850. 6394. 5853. 5620. 5236. 4763. 4488. AZ DOV-BC ". O o 23 -18.31 29 4.70 55 5. 51 2 16 -1.71 w 87 -n10f 7 3 88 46 55 38 34 01 07 21 77 18 40,38 -21. 76 3057 -4.51 2.75 15.45 18.97 2. 17 19.22 21. 31 m 3 -3 co (4 _r. m -0 m~ C 03. +: 3" <A m'* --- -- ~ -— ~ -~ ~ -

The University of Michigan * Engineering Research Institute the trajectory. The actual corrections applied to the DOVAP data on SiMIl 01 are shown in Tables IV, V, and VI and compare the corrected DOVAP and Ballistic Camera data. The difference in absolute position (DOVAP BC) can be summarized as follows. In the x-coordinate, between 65 and 143 feet. In the y-coordinate, between 64 and 129 feet. In the z-coordinate, between -10 and 44 feet, The comparison of data for the layers between grenades shows differences (DOVAP - BC) of Between -6.4 and 17. 3 feet in x Between -11.8 and 7.2 feet in y Between -21. 8 and 21. 3 feet in z. The differences in both absolute position and layers are slightly larger than what might be expected from the index of precisioncG-, T, and T z for the DOVAP data, and the estimated systematic error of the Ballistic Camera data as noted in BRL TN 1157 (referred to above), which states that the unknown systematic error for the Ballistic Camera grenade-burst data varies from 1+ 4 meters at the lower altitudes to better than + 10 meters at the higher altitudes". (The "better" is to be interpreted as less than). Thus, although the data reductions for SMl 01 agree well enough for purposes of the grenade experiment, they do n ct agree as well as they might, theoretically. It is hoped that BRL will make an independent DOVAP data reduction for SM1.01 to check the U of M results, When the data reduction for SM1. 02 through SM2o 10 have been finished, it is planned to re-examine the SM1, 01 data reduction to see if any errors can be found. 3. AIR-SAMPLING EXPERIMENT 3. 1 SCOPE OF THE WORK The quarter was devoted largely to performing control checks on various bottles. The contents of bottles E-2 and C-21-B were analyzed. These two bottles were prepared for flight on Aerobee rockets SC 34 and 35 but were not flown. The helium leak detector was used to determine the leak rates of bottles B-15, B10, C-23-B, B=25, and E-2o 3.2 ANALYSIS OF CONTENTS OF BLI.NK BOTTLES The results of the analysis of the accumulation in E-2 and C-21-B are recorded in Table VII, with calibration runs and entrance tubing checks, I. I t - 11

TABLE VII CONTROL CHECKS ON SAMPLE BOTTLES CCNTP5 Gas in Bottle Sample CCNTP CCNTP (1) 19-1 (1) 19-2 (2) 1 -E-2B-E (2) 2 E-2BE E-2-1 2. 16X10O2 N (1) 20-1:(2) C-21-BE (2)C-21-1 8 6X10-4 (4' B- 1 8.15X10-3,4.2'_1 ~B- 10-3 CCNTP After oxidation with dry-ice trap He Ratio 4.73 3. 85 (3)0. 017 (3)0. 014 4.86 11o 17 (3). 00106 (3)0. 0529 5.7 1.00 1.00 382. 212. 3.48 1.00 78.4 13. 6 0.95 Ne Ratio 1.00 1.00 4.19 2. 7. 2.27 1.42 1.00 1,27 1.76 0.966 % Loss on hot copper filament. 18. 7 19.2 93. 3 91.5 46.7 20.0 97.7 88.8 0.0 Before Ox Vol. lost Liq. N2 11.1 8.4 2,7 36 6 17.9 5.6 % Condensable Material idation After Oxidation c Volo lost Vol. lost Vol lost 2 Dry Ice Liq. N2 Dry Ice ^.... O0.9-5 o _. ' oo 0.90 3 0.9 68.5 2.0 _: 0.6 67.5 0.6 6 1.1 14.6 12.7 4.9 1.2 2,0 9E 62 c i, 0. 84 m 16.4 3 5 10,7 7 4 1.8 m fA m: fi: n C 5 (1) Ground-air controlo (2) Accumulation in Entrance tubing, (3) Liquid N2 Cold Trap. He and Ne Ratios based on CCNTP found with Liquid N2 on cold trap. (4) Ground air introduced into C-21, (5) Total Quantity as computed from system McLeod Readingo

The University of Michigan * Engineering Research Institute Bottle E-2 was believed to have a small leak because a change in pressure was noted on the Pirani gage. This was verified by the quantity of air found in the bottle and subsequent helium leak checks. C-21-B was of an earlier vintage and prepared:for the 1956 flights onl, by fabricating special adaptor rings. It was evacuated about five years previous to the analysis,. This bottle was believed to be as vacuum-tight as C-23-B. It was monitored briefly by operation of its Philipps gage and was found to have accumulated very little gas. 3. 3 BOTTLE LEAK TESTING The results of helium-leak checks on the various bottles are shown in Table VIII. TABLE VIII HELIUM-LEAK CHECKS ON VARIOUS. BOTTLES CCN. TP/Sec C C. NTP/$e"Sec: %' Extra 1He Bottle to account for.. - % found using. accounted for No. extra Me found leak detector by obsereed leak on analysis B-10 7.9 X iO15 2.1 X 1015 I26 B-15 17 X 1015 46 X 10-15 270% C-23-B 1.5 X 10'15 0.028 X 10-15 2% E-2 5.8 X 10-15 2.8 X 1015 48% )B2533. 10-1 33 0% 2)B-25 66 X 10-15 109 X 10-15 165% (1) Upper-Atmosphere Sample (2) Ground Air introduced into Bottle. Up to this time no complete evaluation of the accuracy of the bottle helium-leak rates found with the helium leak detector has been made. However, the results appear to be good and repeated checks of one bottle, using several different collection times, agree very well. The contents of C-23-B flight bottle appear to be the most likely to be a true sample of the atmosphere. -I - 13

The University of Michigan *Engineering Research Institute Associated bottles B-10 and B-15 from the same flight and opened at the same time showed small leaks. Gas from C-23-B contained 24% more helium than the same quantity of ground-air. Gas from B-10 contained 48% more helium than the same quantity of ground air. Correcting B-10 for the helium leak of 26% of the excess helium as indicated in Table II, the gas in B10 would contain only 35% more helium than ground air. This correction brings the helium ratio of B-10 quite close to that of C-23-Bo This reasoning breaks down when B-10 leak rates are studied. The helium leakage rate is observed to be twice the leakage rate required to account for the extra helium found by analysis in the bottle, Since this is one of the earliest leak tests done on the analyzer, the technique may have been faulty. It may be possible to re-check this bottle later. The other possibility presented is that the leak size changed during preparation of the bottle for the leak check. It is hoped this question can be resolvedo No comments will be made on B-25 except to say that the leak predicted by Wanke and Paneth in this bottle was present. Data have not been received indicating the total quantity of gas in the bottle after oxygen removal and the time from sampling to analysis. Therefore, only rough estimates of the actual leakage can be made until the data are available. A comparison of the argon-nitrogen ratio in the upper atmosphere with that of ground air was made using the results reported by Paneth on our samples and the results reported by the Russians. Figure 2 shows the result. It was noted that all points, with one exception lie between the two roughly parallel lines A andB, and the general slope of the lines would seem to indicate increasing separation with altitudeso It is also noted that the Russian results appear to indicate slightly less separation than shown in the American samples. 4. THEORETICAL WORK ON DIFFUSIVE SEPARATION OF GAS MIXTURES IN FLOW FIELDS During this quarter, the analysis of the problem of diffusive separation of gas mixtures in flow fields that is involved in the upper-air sampling experiment has been completed. The results of this research are reported by V. C. Liu in two scientific papers. The first paper, "ANote on Diffusive The fir s t p ~~~~~~~~.11 t. o ifsv Separation of Gas Mixtures in Flow Fields" has been accepted for publication 14

[ The University of Michigan 1.00 o 0.9 0 ~, 0 \ A 00 ' os _ _ _ _ Engineering Research Institute 60 70 80 90 100 ALTITUDE, KM. Fig. 2. Comparison of the University of Michigan (Paneth) and the Russian Sampling Results. 15

The University of Michigan * Engineering Research Institute by the Journal of Applied Physics. The abstract of this paper is quoted in the following paragraphso "This paper discusses the effect of pressure-diffusion flux upon the concentration distribution of gas mixtures in flow fields. The equation of concentration is formulated for a binary gas mixture in which the mass ratio is large and the concentration of the lighter gas is very small. An asymptotic solution to the steady-state equation of concentration is given for an irrotational and is incompressible flow. "As an illustration, the diffusive separation (i.e. deviation from the original homogeneous state) of a mixture of helium and nitrogen along stream lines at the entrance to a long straight channel is calculated. It is assumed that the pressure inside the channel is 90% of that in the free stream; and that the diffusion coefficient of the mixture corresponds with the atmospheric conditions at 80 km altitude." The second paper, "On the Separation of Gas Mixtures by Suction of the Thermal-Diffusion Boundary Layer" reports an accidental discovery of a special diffusion phenomenon which could conceivably lead to a new and more effective (compared to the one which based on Clusius' thermal-diffusion column) method of separating gas isotopes. Last summer, the preliminary manuscript of this paper was sent to Professor Sydney Chapman who since then has announced and reviewed this new result in his lecture at the Gas-Dynamics Symposium of the American Rocket Society held at Northwestern University in August, 1957. This manuscript was then communicated by Professor Chapman for the author to the Quarterly Journal of Mechanics and Applied Mathematics (Oxford) for publication. The abstract of the second paper is given below: "This paper discusses the formation and characteristics of the boundary layer of thermal diffusion that exists along the surface of a heated wall over which a mixture of gases of unequal molecular weights flowso A thermal-diffusion flux is set up in the boundary layer, due to the existence of a temperature gradient, such that the lighter gas tends to move to the hot region and the heavier gas to the cold region. When the temperature of the surface is maintained much higher than that of the free stream, the concentration of the lighter gas increases monotonically from its freestream value at the outer edge of the boundary layer to a maximum value at the plate. "The existence of an extremely high temperature gradient makes it possible to obtain significant diffusive separation of gas mixtures in the boundary layer of a laminar flow; it is from this consideration that the idea 16

- The University of Michigan * Engineering Research Institute of a new method of separating gas mixtures by suction of the thermal-diffusion boundary layer is conceived. An analysis of the thermal-diffusion boundary layer is made, using a flat plate with constant suction as a model and assuming that the concentration of the lighter gas is much smaller than unity. The strong stabilizing effect of suction on the laminar flow is discussed briefly. A limiting ratio of suction vs:free-stream velocity for the maintenance of laminar flow is derived. An estimation of the rate of attaining the equilibrium-concentration profile is also made." 5. LECTURES BY PROFESSOR SYDNEY CHAPMAN A series of lectures on topics of interest to workers in the field of upper-atmosphere research was given by Professor Sydney Chapman during his stay at the University of Michigan. The following copy of the announcement of these lectures describes their content. 17

The University of Michigan * Engineering Research Institute UNIVERSITY OF MICHIGAN PROFESSOR SYDNEY CHAPMAN International President of the Special Committee for the IGY Visiting Professor of Aeronautical Engineering WILL PRESENT A SERIES OF LECTURES. (1957-1958) Nov. 26- "The Solar Corona and the Interplanetary Gas" D6c~ 3 - "The Earth s Atmosphere in the Satellite Region" Dec. 10 — "How Eruptions of Solar Gas Influence the Earth" Dec. 17- "Thermal Diffusion in the Laboratory and in the Solar Corona'" Jan. 7 - "The Electrical Conductivity of the Ionosphere" Jan, 23 - "The International Geophysical Year and the Earth Satellites" First Five Lectures - TUESDAYS, 4:00 PM Auditor-i"rU; C, Angell Hall Sixth Lecture - THURSDAY, 8:00 PM Rackham Amphitheater Auspices of Departments of Aeronautical and Electrical Engineering, Astronomy, Mathematics, and Physics 18

The University of Michigan * Engineering Research Institute LECTURES by PROFESSOR SYDNEY CHAPMAN, noted astronomer, geophysicist and mathematician, is International President of the Special Committee for the International Geophysical Year. He has worked at the Royal Observatory, Greenwich; and at the Universities of Cambridge, Manchester, London, and Oxford, in England; Cairo in Egypt; Istanbul in Turkey, and Gottingen in Germany. In this country he has worked at' he California Institute of Technology and the Universities of Alaska, Michigan, New York, Iowa, and Colorado. His experience fits him to bring to his listeners a comprehensive description of some of the solar and terrestrial problems that occupy astrophysical and geophysical scientists today. Nov. 26- THE SOLAR CORONA AND THE INTERPLANETARY GAS. The sun' s temperature falls from millions of degrees at the center to 60000 at the surface. Above this, the temperature rises again to about a million degrees in the sun's outer atmosphere, called the corona, that becomes visible during a total solar eclipse. The corona extends far outwards from the sun, and it appears likely that it constitutes a hot interplanetary gas through which the earth and other planets move in their orbits. This lecture will be illustrated by a 10-minute movie showing the motions of prominences and the corona at the edge of the sun. This film is one recently prepared at the Sacramento Peak Observatory of the Air Force Cambridge Research Di - rectorate, at Sunspot, New Mexico. Dec. 3 - THE EARTH'S ATMOSPHERE IN THE SATELLITE REGIONo Radio physicists can explore the earth's upper atmosphere to about 200 miles height by radio beams, but above that level the nature of our atmosphere is uncertain. One theory is that the temperature rises to about 1500~C and then remains constant at greater heights. An alternative view will be presented: that the temperature rises to 200, 000, and that above the ionosphere we know, there is an immensely extended layer of atomic hydrogen, beyond which our atmosphere changes to a mixture of protons and electrons and merges with the interplanetary gas. The satellites should be able to decide between these alternatives. 19

- The University of Michigan E Engineering Research Institute Dec. 10 - HOW ERUPTIONS OF SOLAR GAS INFLUENCE THE EARTHo From time to time the sun projects great clouds or streams of hot gas, mainly consisting of protons and electrons, into the space around it. Often the gas impinges on the earth, and causes the visible phenomenon of the northern lights (or aurora borealis) and the invisible phenomena of magnetic storms and disturbances of the ionosphere; these may greatly hinder radio and telegraphic communications. These and other effects of the solar gas on our atmosphere are being actively studied, bringing new discoveries to light. Dec. 17 - THERMAL DIFFUSION IN THE LABORATORY AND IN THE SOLAR CORONAo Whenever a gas consists of more than one constituent, a gradient of temperature will cause a diffusive flow tending to change the composition between differen, regions. This property, called thermal diffusion, is much used to separate rare iostopes, in chemical laboratories and atomic energy establishments. It can also be disturbing phenomenon in chemical experiments on mixed gases. Moreover it occurs in mixed gases in nature - in our atmosphere and in that of the sun. It seems likely to be of much importance in the solar corona. Jan. 7 - THE ELECTRICAL CONDUCTIVITY OF THE IONOSPHEREo Many substances, such as wood and (especially) crystals, have elastic or optical properties that are different in directions. An ionized gas in a magnetic field likewise has this feature, as regards its electrical conductivity. The ionosphere is such a gas. The peculiarities of its electrical conductivity have interesting consequences. One of these was known long before the cause was understood - it is an enhancement of the daily magnetic variation on the magnetic equator. Jan. 23- THE INTERNATIONAL GEOPHYSICAL YEAR AND THE EARTH SATELLITES. (Announcement to follow.) 20

The University of Michigan * Engineering Research Institute 6. LABORATORIES VISITED Ft. Churchill, Manitoba, Canada. U. S. Army Signal Engineering Laboratories 7. ACKNOWLEDGEMENTS We are indebted to the Meteorological Branch of the U. S. Army Signal Engineering Laboratories for continued collaboration and support. The success of the ten firings of the Aerobee "Grenade" experiment at Ft. Churchill are due to a very large measure to the superb facility for upperair research which is located there. We are deeply indebted to the work of all of the groups at Ft. Churchill who contributed so much effort to insure the success of our firings.

UNIVERSITY OF MICHIGAN 90111 111115 02228 9964 3 9015 02228 9964