Question

TOPIC: NORMAL STATIONARY SHOCKS 3. Exhaust gases from a rocket engine have MW 14 kg/kmol. Assume them to be perfect gas with y = 1.25. These gases are accelerated through a converging-diverging nozzle. A normal shock occurs at a section where M 2.0. Find pressure, temperature, density and stagnation pressure ratio across this shock wave

Answer 1

C 3.1.3 Normal Shock Standard Soy able 3.3: Starci Slock Standard Talie fur k=1.1 Mix | M. ΡΟς 1.0000 1.0000 11.0000 1.0000 1.0000 1.0000 1.0100 0.99013 1.0167 1.0066 1.0235 1.00000 1.0200 09.98052 1.0334 1.0132 1. 071 (1.99999 1.0300 0.97115 1.0198 1.0502 1.0711 (1.99997 1.0400 0.96203 1.0263 1.0671 1.0952 0.99992 1.0500 0.95313 1.0328 | 1.0840 1.1196 0.99985 1.0600 0.94445 1.0393 1.1009 11.1442 0.99975 1.0700 0.9359810458 T 1.1179 11.1091 0.99961 i M. 1.0800 1.0900 1.1000 1.2000 1.2500 1.3000 1.3.500) 1. 1000 1.-1300 1.5000 1.5500 1.6000 1.6500 1.7000 1.7500 1.8000 1.8700) 1.9000 1.9500 2.0000 2.1000 2.2000 2.3000 2.1000 2.5000 2.6000 2.7000 2.8000 2.9000 3.0000 3.5000 1.0000 1 2 0.92771 1.0322 0.91965 1 1.0586 0.91177 1.0649 0.84217 1.1280 0.81264 1.1591 0.78596 1.1909 0.70175 1.2226 01.73971 1.25-17 (1.71956 1.2872 0.701091.3202 0.68110 1.3538 0.668441 1.3880 0.65396 1.4228 0.6405.1 1.1583 0.628091 1.1946 0.651 650) 1.5316 0.60570 1.5693 11.59502 1.6079 0.58618 1.6473 0.37725 1.6875 0.56128 1.7705 0.5-1706 1.8569 (..3.3-111 1.9468 0,523122 2.0-103 0.51299 2.1375 0.50387 2.2383 0.-19563 2.3129 ().48817 2.4512 0.-18138 2.5632 0.-17519 2.6790 (1.15115 3.3151 0.13 1916 1.0.169 1.1349 1.1520 1.1691 1.3416 1.1286 1.5157 1.6028 L6897 1.7761 1.8021 1.9.173 2.0317 2.1152 2.1977 2.2791 2.3592 2. 381 2.5157 2.5919 2.6667 2.8119 2.9512 3.08 3.2119 3.3333 3. 1490 3.5390 3.6636 3.7629 3.8571 1.2009 1.571.1 1.19-11 1.2195 1.2150 1.5133 1.6562 1.8050 1.09596 2.1200 2.2863 2.1583 2.6363 2.8200 3.0096 3.2050 3.1003 3.6133 3.3263 1.04150 1.2696 1.5000 1.9783 5. IS00 0.0050 6.5533 7.1250. 7.7200 8.3383 8.9800 9.6450 -10.3333 11.1250 18.3000 Po 0.99943 0.99920 0.99893 0.99280 0.98706 0.97937 0.96971 0.95819 0.9118 0.92979 0.91319 0.89520 0.87599 0.85572 0.83-157 **** 081208 0.79023 076736 0.74420 0 720SZ 0.67-120 0.6281-1 0.-14017 019901 0.46012 0.42359 (1.38946 0.35773 01:32831 0.21295 11.13576 | 23. 1553 20.000 MX 4.5000 5.0000 15.5000 6.0000 326 3000 70000 IS119 35.0000) 5.1 ISS) 5.2683 5.3651 5.1111 :3 ATX 0.1237,5 1.871 0,1155223 5.000 7). T0897 6. N219 0.10 116 7.0 1010 0.10038 9.15 0,39736 10), 165 (1.375.17 0.330230133.3967 71.331121 11,338681 16.69 L . 07.387LS 203399 11. 3 1!). 120 01.0917) 0.00172 11.1280 0.0296 1.11211 37 SO010 0.OUSE OLOGI 73.300 TEST .6751 1. 3:1 15. GS 1.711 TT222 7.070301 10

Pulp 143), a For mach No=2 Cal gas Let x po be point before shock & y be point after shack. , we have For mormal shock In My v lt8-1 My For mm= 2.7 from chart My = 0.57735 Ty = 1.6875 , S 2-6667, Py = 45 , boy 0 72087 I + Ym? = 1+ 1.25x2? 1+ ym2 It 7:258o.517352 = 4.235 = (1+) my 2(8-1) 2. 252 = 1.5839 4o.5 2 (0.25) - 1.444

S - RAT SAT = 2.9315, की 34.235 1-444 - 1.2264 .25/10/25 ... (14 . (0232) 27-53325 Poy - 22-64X 4.2359-068395 7.5-4375