static pressure

| January 29, 2015

An aircraft flies with a Mach number Ma1 = 0.8 at an altitude of 7000 m where the pressure is 41.1 kPa and the temperature is 242.7 K. The diffuser at the engine inlet has an exit Mach number of Ma2 = 0.3. For a mass flow rate of

65 kg/s, determine the static pressure rise across the diffuser and the exit area.

Get a 5 % discount on an order above $ 150
Use the following coupon code :
2018DISC
speed of sound
heat transfer

Category: Coursework

Our Services:
Order a customized paper today!