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Unformatted text preview: t is qualitatively correct and clearly label the angle the jet makes relative to the exit. b. At another condition the back pressure is 65 kPa. Calculate the Mach number, pressure, and the angle of the jet boundary just after the wave shed from the nozzle exit. Sketch the flow in the jet such that it is qualitatively correct and clearly label the angle the jet makes relative to the exit. c. Which value of back pressure (30 kPa, 65 kPa) generates an oblique shock in the jet? A shock wave will reflect off the centerline of the jet. Calculate the Mach number and pressure after the reflected shock. 2. Consider a supersonic airfoil flying at a Mach number of 2.5 at an altitude where the pressure is 50 kPa. The airfoil is a diamond shape...
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- Spring '14