ella We wish to design a supersonic wind tunnel that produces a Mach 2.95 flow at standard sea level conditions in the t

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Ella We Wish To Design A Supersonic Wind Tunnel That Produces A Mach 2 95 Flow At Standard Sea Level Conditions In The T 1 (73.64 KiB) Viewed 21 times

Ella We Wish To Design A Supersonic Wind Tunnel That Produces A Mach 2 95 Flow At Standard Sea Level Conditions In The T 2 (23 KiB) Viewed 21 times

ella We wish to design a supersonic wind tunnel that produces a Mach 2.95 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 T, M т 0.2550 +01 0.1847 +02 0.8027+01 0.2300 +01 0.2763 +01 0.2600+01 0.1995 +02 0.8484 +01 0.2352 +01 0.2896 +01 0.2650+ 01 0.2156+02 0.8965 +01 0.2404 +01 0.3036+01 0.2700+01 0.2328+02 0.9472+01 0.2458 +01 0.3183+01 0.2750 +01 0.2514+02 0.1001+02 0.2512 +01 0.3338 +01 0.2800+01 0.2714 +02 0.1057+02 0.2568 +01 0.3500+01 0.2850 +01 0.2929+02 0.1116+02 0.2624 +01 0.3671 +01 0.2900+01 0.3159 +02 0.1178 +02 0.2682 +01 0.3850+01 0.2950 +01 0.3407+02 0.1243 +02 0.2740+01 0.4038+01 0.3000+01 0.3673 +02 0.1312+02 0.2800+01 0.4235 +01 0.3050 +01 0.3959 +02 0.1384 +02 0.2860+01 0.4441 +01 0.3100+01 0.4265 +02 0.1459+02 0.2922 +01 0.4657 +01 0.3150 +01 0.4593 +02 0.1539+02 0.2984 +01 0.488401 0.3200+01 0.4944 +02 0.1622 +02 0,304801 0.5121 +01 0.3250 +01 0.5320 +02 0.1709 +02 0.3112+01 0.5369+01 0.3300+01 0.5722 +02 0.1800+02 0.3178 +01 0.5629+01 0.3350 +01 0.6152+02 0.1896 +02 0.3244 +01 0.5900+01 0.3400+01 0.6612 +02 0.1996 +02 0.3312 +01 0.6184 +01 0.3450 +01 0.7103+02 0.2101 + 02 0.3380 +01 0.6480+01 0.3500+01 0.7627+02 0.2211 +02 0.3450 +01 0.6790+01 PI Normal Shock Properties M 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 0.3300 +01 0.1254 +02 0.3350 + 01 0.1293 +02 0.3400 + 01 0.1332 +02 0.3450+01 0.1372 +02 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 0,4112 +01 0.4151 +01 0.4188 +01 0.4225 +01 T; T 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 0.3049+01 0.3114 +01 0.318001 0.3247 +01 Po 0.499000 0.4793 +00 0.4601 +00 0.4416 +00 0.4236+00 0.4062 +00 0.3895 +00 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 0.2533 +00 0.2425 +00 0.2322 +00 0.2224 +00 P 0.8526+01 0.8850+ 01 0.9181+01 0.9519+01 0.9862 +01 0.1021 +62 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 0.1449+02 0.1492 +02 0.1535 +02 0.1579+02 0.513 OSO 0503 0.495 0.495 0.491 0.48 0.484 0.481 0.47% 0.475 0472 0.466 0.46€ 0.464 0.461 0455 0.457 0455 0.453
The reservoir pressure is atm. The reservoir temperature is | 'R. The nozzle throat area is JA? ? The nozzle exit area is ft2 The diffuser throat area is ft?