Answer Happy

A ele 8 We wish to design a supersonic wind tunnel that produces a Mach 3 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 T 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 0.275001 0.2514+02 0.1001+02 0.2512 +01 03338 +01 0.2800+01 0.2714+02 0.1057 +02 0.2568+01 0.3500+01 0.2850 +01 0.2929402 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 0.300001 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 0.162202 0,3048 +01 0.5121 +01 0.3250+ 01 0.5320+02 0.1709 +02 0.3112 +01 0.5369+01 0.3300+01 0.5722 +02 0.180) +02 0.3178.+01 0.5629+01 0.3350 +01 0.6152+02 0.1896402 0.3244 +01 0.5900+01 0.3400+01 0.6612+02 0.1996 +02 0.331201 0.6184 +01 0.3450 401 0.7103+02 0.2101 +02 0.3380+01 0.6480+01 0.350001 0.7627+02 0.2211 +02 0.6790+01 + + + 10+ OSTEO
Normal Shock Properties ब M P2 PI ASI M2 PI 0.2500+01 0.7125 +01 0.3333 +01 0.2550 +01 0.7420+01 0.3392 +01 0.2600+01 0.7720+01 0.3449+01 0.2650 + 01 0.8026 +01 0.3505 +01 0.2700+01 0.8338+01 0.3559+01 0.2750 +01 0.8656 +01 0.3612+01 0.2800+01 0.8980+01 0.3664 +01 0.2850+01 0.9310+01 0.3714 +01 0.2900 +01 0.9645 +01 0.3763 +01 0.2950+01 0.9986 +01 0.3811 +01 0.3000+01 0.1033+02 0.3857 +01 0.3050+01 0.1069 +02 0.3902+01 0.3100+01 0.1104+02 0.3947 +01 0.3150+ 01 0.1141 +02 0.3990+01 0.3200+01 0.1178 +02 0.4031 +01 0.3250+ 01 0.1216 +02 0.4072 +01 0.3300+01 0.1254 +02 0.4112+01 0.3350 +01 0.1293 +02 0.4151 +01 0.3400+01 0.1332 +02 0.4188 +01 0.3450+01 0.1372 +02 0.4225 +01 The reservoir pressure is 36.73 atm. T: Ti 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 0.3180+01 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 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 0.1449 +02 0.1492 +02 0.1535 +02 0.1579+02 0.5130 +00 0.5083 +00 0.5039 +00 0.4996 +00 0.4956 +00 0.4918 +00 0.4882 +00 0.4847 +00 0.4814 +00 0.4782 +00 0.4752 +00 0.4723+00 0.4695 +00 0.4669 +00 0.4643+00 0.4619 +00 0.4596 +00 0.4573 +00 0.4552 +00 0.4531 +00 The reservoir temperature is 1453.2 PR. The nozzle throat area is 0.3451 12. The nozzle exit area is 0.1462112