22056_1_homeWork5

22056_1_homeWork5 - ME4240:Gas Dynamics Home Work 5 Due...

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ME4240 :Gas Dynamics Home Work 5, Due Friday the 13th of November November 5, 2009 1. A wedge of 25 degree half-angle is immersed in a supersonic flow. Flow visualizations indicate that the oblique shock wave is attached and is at an angle of 50 degrees to the incident flow. Based on this information calculate the Mach number of the incident supersonic flow. 2. Calculate the maximum surface pressure (in N/m 2 ) that can be achieved on the forward face of a wedge flying at Mach 3 in standard sea level conditions ( P atm =101325 N/m 2 ) with an attached shock wave. 3. Consider the supersonic airflow between two parallel walls at M =2.2, p =45kPa and T =300K. A positive deflection of 24 o is imposed on on of the walls as shown in Figure 1 (a) Draw the waves produced by the deflection and the interaction with the opposite wall. On the same drawing also draw the streamlines. (b) Calculate the flow properties past the reflected wave: Mach number, static and total pressure, total temperature and entropy change.

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