Air at 10km altitude initially travelling at hypersonic speed is decelerated through a normal shockwave. The deceleration caused a velocity of 1600km/hr after the wave. a) What is the upstream mach number? O 7.98 O 6.44 O 8.30 9.54 10.22 b) What is the upstream velocity? 2585.97 m/s 2885.96 m/s O 2122.66 m/s O 2485.44 m/s 2335.11 m/s
Air at 10km altitude initially travelling at hypersonic speed is decelerated through a normal shockwave. The deceleration caused a velocity of 1600km/hr after the wave. a) What is the upstream mach number? O 7.98 O 6.44 O 8.30 9.54 10.22 b) What is the upstream velocity? 2585.97 m/s 2885.96 m/s O 2122.66 m/s O 2485.44 m/s 2335.11 m/s
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Transcribed Image Text:Air at 10km altitude initially travelling at
hypersonic speed is decelerated through a normal
shockwave. The deceleration caused a velocity of
1600km/hr after the wave.
a) What is the upstream mach number?
O 7.98
6.44
O 8.30
9.54
10.22
b) What is the upstream velocity?
2585.97 m/s
O 2885.96 m/s
2122.66 m/s
2485.44 m/s
O 2335.11 m/s
Transcribed Image Text:c) What is the downstream pressure?
2585548.54 Pa
2232645.32 Pa
2425627.55 Pa
2132458.65 Pa
2111409.46 Pa
d) What is the downstream density?
5.958 kg/m^3
5.593 kg/m^3
5.454 kg/m^3
5.124 kg/m^3
5.369 kg/m^3
e) What is the downstream temperature?
3252.69 K
3478.88 K
3585.22 K
3198.89 K
2985.32 K
f) What is the downstream Speed of Sound?
1134 m/s
1332 m/s
1452 m/s
1035 m/s
1652 m/s
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