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1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature of 250 K, expands around a 10
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature of 250 K, expands around a 10 degrees convex corner. Determine the downstream Mach number M,, pressure p, , temperature T,, and the fan angle. Fan angle Fio
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Thermodynamics An Interactive Approach
Authors: Subrata Bhattacharjee
1st edition
130351172, 978-0130351173
