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42 Figure 15. The dispersion of the measured values is again due substantially to the poor behavior of the recording drum. The burning rate of the cordite follows more or less a po.75-HO.7s iaw j" o r the Cpowder an exponent of 0.53 best fits the results. Several theoretical works were also carried out. Figure 16 shows, for instance, the results of a theory developed for the calculation of the pressure distribution within the hole of a tubular charge for a burning rate given by ap n . The coefficient £ is given where 8 is the propellant density, r the hole radius assumed constant, and T the gas temperature at the burning surface. R and y have the conventional meanings. The distance from the middle section of the hole is indicated by s. The terminal points on each curve correspond to choked conditions at the two ends of the hole (this way my first contact with the fundamental importance of Mach 1 even in the presence of combustion phenomena). Choking ap- FIGURE 14.—Front view of the pendulum test stand with chamber. c 2 (A E o 1.5 0 1.5 0.5 -- - - _ .1 B • C * 0 * 6 • >. • 1 • LA O * / / • — — o ' /b — — __ — — SMITHSONIAN ANNALS OF FLIGHT 1 - -- .... — '/ / / / ... 1 / / / • v' • * /* • • i / < rf> • / ' # o • — — .... — i / _.. .._. y "" / .s / JRDITE T — 100 200 K ^ * • t i A 1 1 1 1 P0LVERE C - - — — ... _. - _ 150 200 FIGURE 15.—Burning rates for cordite (top) and for C-powder. pears for a certain charge length, beyond which no steady solution to the problem exists and the pressure must steadily rise in the hole. It seemed to me at first that this was an important finding, and I was disappointed when I calculated that for the actual charges the maximum value of the abscissa —
NUMBER 10 - / 1 1 n-1 / / / / / / 57 i -^ s ( , P 200 150 00 SO 0 4 3 2 1 0 1 2 3 |p.| n = 0.5 / / i 60 SO 40 30 " E a 200 P 150 100 50 0 E 'C 0 - 50 1 Jt>\ ^s0 ^s s'* 7 \ *A 0 v \ A fr \ \ \ \ \ V
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Page 4 and 5: A Bibliographic Note The series Smi
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Page 11 and 12: 1 Some Jet Propulsion Formulas of O
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Page 18 and 19: During these years, in which the fu
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Page 28 and 29: 18 3. French Patent 318,667, 13 Feb
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Page 33 and 34: Appendix Considerations Concerning
Page 35 and 36: NUMBER 10 In the present case, ther
Page 37 and 38: NUMBER 10 27 III Let us consider wh
Page 39 and 40: NUMBER 10 29 = 2100 sec, the rate w
Page 41: NUMBER 10 31 bring us far away from
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Page 67 and 68: Robert H. Goddard and the Smithsoni
Page 69 and 70: NUMBER 10 to help Mr. Goddard in de
Page 71 and 72: NUMBER 10 61 flash powder which mig
Page 73 and 74: NUMBER 10 63 FIGURE 5.—Modificati
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Page 77 and 78: NUMBER 10 tion for a U.S. patent on
Page 79: NUMBER 10 69 70. Goddard to Abbot,
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Page 85 and 86: Recollections of Early Biomedical M
Page 87 and 88: NUMBER 10 r FIGURE 2.—First biome
Page 89 and 90: FIGURE 4.—Presentation by Dr. Con
Page 91 and 92: Astrodynamics is defined in terms o
Page 93 and 94: NUMBER 10 83 But it should be recog
Page 95 and 96: NUMBER 10 85 were experimenting in
Page 97 and 98: Vladimir Mandl: Founding Writer on
Page 99 and 100: NUMBER 10 89 PATENTNl OftAD REPUBLI
Page 101 and 102: 10 Developments in Rocket Engineeri
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NUMBER 10 93 FIGURE 2.—The first
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NUMBER 10 FIGURE 4.—The ORM-9 eng
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NUMBER 10 97 FIGURE 9.—ORM-50 eng
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NUMBER 10 99 Section along AA Firin
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NUMBER 10 101 FIGURE 13.—The expe
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11 A Historical Review of Developme
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NUMBER 10 105 FIGURE 5.—Lithergol
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NUMBER 10 that the possibility of a
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NUMBER 10 109 the contrary; we then
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NUMBER 10 111 rocket combustion cha
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12 On the GALCIT Rocket Research Pr
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NUMBER 10 115 The undertaking we ha
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NUMBER 10 117 advise on the support
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NUMBER 10 methyl-alcohol rocket mot
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NUMBER 10 121 5. "Rocket Performanc
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NUMBER 10 123 FIGURE 5.—Overall v
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NUMBER 10 on the possibility of usi
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NUMBER 10 33. Letters (note 14). 34
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130 SMITHSONIAN ANNALS OF FLIGHT ce
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132 SMITHSONIAN ANNALS OF FLIGHT of
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134 SMITHSONIAN ANNALS OF FLIGHT A
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136 SMITHSONIAN ANNALS OF FLIGHT Re
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138 SMITHSONIAN ANNALS OF FLIGHT FI
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140 SMITHSONIAN ANNALS OF FLIGHT ca
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144 SMITHSONIAN ANNALS OF FLIGHT 2
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146 SMITHSONIAN ANNALS OF FLIGHT St
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148 SMITHSONIAN ANNALS OF FLIGHT A-
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150 SMITHSONIAN ANNALS OF FLIGHT CH
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152 SMITHSONIAN ANNALS OF FLIGHT LI
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15 Ludvik OcenaSek: Czech Rocket Ex
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NUMBER 10 159 FIGURE 2.—Ludvik Oc
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NUMBER 10 161 FIGURE 5.—Ludvik Oc
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NUMBER 10 163 FICURE 6.—a, Launch
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NUMBER 10 165 quarry near Prague. E
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168 SMITHSONIAN ANNALS OF FLIGHT re
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170 SMITHSONIAN ANNALS OF FLIGHT I
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172 SMITHSONIAN ANNALS OF FLIGHT Th
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174 SMITHSONIAN ANNALS OF FLIGHT Ve
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17 First Rocket and Aircraft Flight
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NUMBER 10 179 The rocket project wa
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NUMBER 10 181 FIGURE 2.—Second st
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NUMBER 10 FIGURE 3.—DM-2 ramjet e
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18 On Some Work Done in Rocket Tech
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NUMBER 10 187 FICURE 3.—Launching
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NUMBER 10 189 on the smoked tape. A
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NUMBER 10 191 FIGURE 9.—Indicatin
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NUMBER 10 193 FIGURE 13.—Control
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NUMBER 10 195 2000 rpm by rotating
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NUMBER 10 197 Lubricant ^ 9a' " FIG
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NUMBER 10 199 of radio signals to t
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NUMBER 10 201 1. Register of experi
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204 SMITHSONIAN ANNALS OF FLIGHT te
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206 SMITHSONIAN ANNALS OF FLIGHT be
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208 SMITHSONIAN ANNALS OF FLIGHT 6.
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212 SMITHSONIAN ANNALS OF FLIGHT 3-
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A^ -/••••••.\ D+ VE •
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216 SMITHSONIAN ANNALS OF FLIGHT NO
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218 SMITHSONIAN ANNALS OF FLIGHT Vi
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222 SMITHSONIAN ANNALS OF FLIGHT Co
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224 SMITHSONIAN ANNALS OF FLIGHT Al
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226 SMITHSONIAN ANNALS OF FLIGHT de
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228 SMITHSONIAN ANNALS OF FLIGHT Th
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230 SMITHSONIAN ANNALS OF FLIGHT wi
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232 SMITHSONIAN ANNALS OF FLIGHT th
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234 SMITHSONIAN ANNALS OF FLIGHT wa
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236 SMITHSONIAN ANNALS OF FLIGHT In
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238 SMITHSONIAN ANNALS OF FLIGHT ab
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240 diesel fuel and lox began on th
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242 14 May 1940: Reviewed layout fo
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248 SMITHSONIAN ANNALS OF FLIGHT th
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250 SMITHSONIAN ANNALS OF FLIGHT tl
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NUMBER 10 253 FIGURE 6.—a, Model
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NUMBER 10 255 FIGURE 9.—Winged ro
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NUMBER 10 257 6. Small gyroscopic a
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262 SMITHSONIAN ANNALS OF FLIGHT N?
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264 B C FIGURE 7.—Drawing from Sw
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266 SMITHSONIAN ANNALS OF FLIGHT in
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24 Some New Data on Early Work of t
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NUMBER 10 271 jy.. FIGURE 3. /# £
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NUMBER 10 273 conclusions, which we
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NUMBER 10 275 thrust engines. A for
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25 Early Developments in Rocket and
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NUMBER 10 279 Time reference 5 sec
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NUMBER 10 281 During measurement of
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NUMBER 10 283 First Personal Involv
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NUMBER 10 285 on the Wasserkuppe, o
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288 SMITHSONIAN ANNALS OF FLIGHT Ch
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27 Annapolis Rocket Motor Developme
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NUMBER 10 297 I remember being so f
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NUMBER S P. (P»i) P, (psi) Po (psi
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NUMBER 10 301 Figure 6 shows these
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304 Frank-Kamenetskiy, D.A., 193 Fr
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306 SMITHSONIAN ANNALS OF FLIGHT Ro
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TUT10N NOIifUIISNt NVINOSHlitNS S3f
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