We wish to design a supersonic wind tunnel that produces a Mach 3.15 flow at standard sea level conditions in the test s

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We Wish To Design A Supersonic Wind Tunnel That Produces A Mach 3 15 Flow At Standard Sea Level Conditions In The Test S 1 (75.99 KiB) Viewed 32 times

We Wish To Design A Supersonic Wind Tunnel That Produces A Mach 3 15 Flow At Standard Sea Level Conditions In The Test S 2 (40.13 KiB) Viewed 32 times

We wish to design a supersonic wind tunnel that produces a Mach 3.15 flow at standard sea level conditions in the test section and has a mass flow of air equal to 1 slug/s. Calculate the necessary reservoir pressure and temperature (Round the final answer to two decimal places.), the nozzle throat and exit areas, and the diffuser throat area. (Round the final answer to four decimal places.) The tables for isentropic flow properties and normal shock properties are given below. Isentropic Flow Properties & M 0.2550 +01 0.2600+01 0.2650 +01 0.2700+01 0.2750 +01 0.2800+01 0.2850 +01 0.2900 +01 0.2950 +01 0.3000+01 0.3050+01 0.3100+01 0.3150+01 0.3200+01 0.3250 +01 0.3300+01 0.3350 +01 0.3400+01 0.3450 +01 0.3500 +01 0.1847 +02 0.1995 - 02 0.2156+02 0.2328 +02 0.2514 +02 0.2714+02 0.2929 +02 0.3159+02 0.3407 +02 0.3673 +02 0.3959 +02 0.4265 +02 0.4593 +02 0.494402 0.5320 +02 0.5722 +02 0.6152 +02 0.6612+02 0.7103+02 0.7627+02 0.8027+01 0.8484 +01 0.8965 +01 0.9472 +01 0.1001+02 0.1057+02 0.1116 +02 0.1178 +02 0.1243 +02 0.1312 +02 0.1384 +02 0.1459 +02 0.1539+02 0.1622 +02 0.1709+02 0.1800+02 0.1896 +02 0.1996 +02 0.2101+02 0.2211 +02 Ť 0.2300+01 0.2352 +01 0.2404 +01 0.2458 +01 0.2512 +01 0.2568+01 0.2624 +01 0.2682 +01 0.2740+01 0.2800+01 0.2860+01 0.2922 +01 0.2984 +01 0_3048 +01 0.3112+01 0.3178 +01 0.3241 +01 03312-01 0.3380 +01 0_3450+01 0.2763 +01 0.2896 +01 0.3036+01 0.3183+01 0.3338 +01 0.3500+01 0.3671 +01 0.3850 +01 0.4038+01 0.4235 +01 0.4441 +01 0.4657+01 0.4884 +01 0.5121 +01 0.5369 +01 0.5629+01 0.5900 +01 0.6184 +01 0.6480 +01 0.6790+01 T: SIS Po Pi Po Normal Shock Properties M P2 Pi 0.2500+01 0.7125 +01 0.2550 +01 0.7420 +01 0.2600+01 0.7720 +01 0.2650+01 0.8026 +01 0.2700+01 0.8338 +01 0.2750 +01 0.8656 +01 0.2800+01 0.8980 +01 0.2850 +01 0.9310 +01 0.2900 +01 0.9645 +01 0.2950+01 0.9986 +01 0.3000+01 0.1033 + 02 0.3050+ 01 0.1069+02 0.3100+01 0.1104+02 0.3150+01 0.1141 +02 0.3200+01 0.1178 +02 0.3250 +01 0.1216 +02 P2 PI 0.3333 +01 0.3392 +01 0.3449+01 0.3505 +01 0.3559+01 0.3612 +01 0.3664 +01 0.3714 +01 0.3763 +01 0.3811 +01 0.3857 +01 0.3902 +01 0.3947 +01 0.3990+01 0.4031 +01 0.4072+01 0.2137+01 0.2187 +01 0.2238+01 0.2290+01 0.2343 +01 0.2397+01 0.2451 +01 0.2507 +01 0.2563 +01 0.2621 +01 0.2679+01 0.2738+01 0.2799-01 0.2860 + 01 0.2922 +01 0.2985+01 0.4990+00 0.4793 +00 0.4601+00 0.4416 +00 0.4236+00 0.4062 +00 0.389500 0.3733+00 0.3577 +00 0.3428 +00 0.3283 +00 0.3145+00 0.3012+00 0.2885 +00 0.2762 +00 0.2645 +00 0.8526+01 0.8850 +01 0.9181+01 0.9519 +01 0.9862 +01 0.1021 +02 0.1057+02 0.1093 +02 0.1130 +02 0.1168 +02 0.1206+02 0.1245 +02 0.1285 +02 0.1325+02 0.1366 +02 0.1407 +02 0.51 0.50 0.50 0.491 0.49 0.49 0.48 0.48 0.48 0.471 0.47 0.47 0.46! 0.464 0.46 0.46
0.3100+ 01 0.3150+01 0.3200+ 01 0.3250+ 01 0.3300 + 01 0.3350 + 01 0.3400+01 0.3450 +01 0.1104 +02 0.1141 +02 0.1178 +02 0.1216 +02 0.1254 +02 0.1293 +02 0.1332 +02 0.1372 +02 0.3947 +01 0.3990 +01 0.4031 +01 0.4072 +01 0.4112 +01 0.4151 +01 0.4188 +01 0.4225 +01 0.2799 + 01 0.2860 + 01 0.2922 +01 0.2985 +01 0.3049+01 0.3114 +01 0.3180+01 0.3247 +01 0.3012 +00 0.2885 +00 0.2762 +00 0.2645 +00 0.2533+00 0.2425 +00 0.2322 +00 0.2224 +00 0.1285 +02 0.1325 +02 0.1366 +02 0.1407 +02 0.1449 +02 0.1492 +02 0.1535 +02 0.1579+02 0.46: 0.461 0.46 0.46 0,45 0.45 0.45: 0.45 The reservoir pressure is 97187.88 atm. The reservoir temperature is 1548.7 R. The nozzle throat area is 0.0218 ft2 The nozzle exit area is 0.1066 ft2 The diffuser throat area is 0.0755 72