Engineering, 21.08.2019 01:30 cece9080
Anormal shock wave takes place during the flow of air at a mach number of 1.8. the static pressure and temperature of the air upstream of the shock wave are 100 kpa (abs.) and 150c. determine the mach number, pressure and temperature downstream of the shock.
Answers: 3
= Specific Heat ratio of air
![\frac{T_{1}}{T_{o}}=\frac{[2\gamma M^{2}-(\gamma -1)][(\gamma -1)M^{2}+2]}{(\gamma +1)^{2}M^{2}}](/tpl/images/0183/3642/b260b.png)
![\frac{T_{1}}{423}=\frac{[2\times 1.4\times 1.8^{2}-(1.4-1)][(1.4-1)1.8^{2}+2]}{(1.4+1)^{2}\times 1.8^{2}}\\\\\therefore \frac{T_{1}}{423}=1.53\\\\\therefore T_{1}=647.85K=374.85^{o}C](/tpl/images/0183/3642/bf1c9.png)
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Anormal shock wave takes place during the flow of air at a mach number of 1.8. the static pressure a...
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