Answer Happy

3 1 points 8 04.06.26 SIL Book + We wish to design a supersonic wind tunnel that produces a Mach 3.2 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 sentropic flow properties and normal shock properties are given below. Isentropic Flow Properties A M T A- 0.2550 +01 0.1847 +02 0.8027+01 0.2800+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 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 0.459302 0.1539+02 0.298.4+01 0488401 0.3200+01 0.4944+02 0.1622 +02 0.3048+01 0.5121 +01 0.3250 +01 0.532002 0.1709+02 03112 +01 0.5369 01 0.3300+01 0.5722 +02 0 1800+02 03178 +01 0.5629+01 0.3350 +01 0.6152+02 0.1896+02 0.3244 +01 0.590001 0.3400+01 0.6612+02 0.1996 +02 0331201 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 0.679001 + Hint + + + References + EIE T: 71 M PI Normal Shock Properties 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 0.270001 0.8338+01 0.3333 +01 0.3392 +01 0.3449+01 0.350501 0.2137+01 0.2187 +01 0.2238+01 0.2290+01 0.2343 +01 0.499000 0.4793 +00 0.4601+00 0.4416 +00 0.4236 +00 08526+01 OXX50+01 0.9181+01 0.9519 +01 0.9862+01 0.513000 0.5083 +00 0.5039+00 0.4996 +00 0.495600 + 10+ OSSED +

3 0.3450+01 0.3500+01 0.7103+02 0.7627+02 0.2101 +02 0.2211 +02 0.3380 +01 0.3450 +01 0.6480+01 0.6790+01 Normal Shock Properties M P2 M: points PI PI Po, PI 04:06:23 eBook 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 The reservoir pressure is 000 Hint T: Ti 0.2137+01 0.2187+01 0.2238+01 0.2290 + 01 0.234301 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 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 0.4990 + 00 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 Print References atm. The reservoir temperature is R. The nozzle throat area is 12 The nozzle exit area is ft2 The diffuser throat area is ft2