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Tuesday, 22 September 2015
RTU B.Tech Fundamentals of Aerodynamics previous year question of 2012
Consider a normal shock wave in a supersonic air stream where the pressure upstream of the shock is 1 atm. Calculate the loss of total pressure across the shock wave when the upstream match number is M1 = 2.
B.Tech, Fundamentals of Aerodynamics
2012
Define the equation for static pressure ratio across two shock.
B.Tech, Fundamentals of Aerodynamics
2012
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