Aerodynamics
Calculate the Mach number of the expanded exhaust for an ideal
scramjet flying at Mach 8 at an altitude of 40,000 m. The inlet has
two ramps of 10 degrees each, followed by a reflected shock with 20
degree turning angle. Fuel to air ratio is 1:50 and the fuel
releases 44,000 kJ/kg of energy. The cross-sectional area of the
combustion chamber is 1/10 that of the scramjet area.
Aerodynamics Calculate the Mach number of the expanded exhaust for an ideal scramjet flying at Mach 8 at an altitude of
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Aerodynamics Calculate the Mach number of the expanded exhaust for an ideal scramjet flying at Mach 8 at an altitude of
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