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Physics, 30.09.2019 21:10 kyusra2008

Consider the purely subsonic flow in a convergent-divergent duct. the inlet, throat and exit area are l m^2, 0.7 m^2 and 0.85 m^2, respectively. if the inlet mach number and pressure are 0.3 and 0.8 times 10^5 n/m^2, respectively, calculate: a) m and p at the throat, (b) m and p at the exit.

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Consider the purely subsonic flow in a convergent-divergent duct. the inlet, throat and exit area ar...
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