The entrance air temperature to the combustion chamber of a SCRAMjet engine is limited to 2800 R; above this temperature, dissociation of the air and decomposition of the fuel in the combustion chamber cause a loss of available energy and reduction of thrust. Consider a SCRAMjet powered hypersonic vehicle flying at Mach 10 at an altitude of 130,000 ft. Calculate the lowest Mach number to which the flow in the inlet can be slowed before entering the combustor.
We need at least 10 more requests to produce the solution.
0 / 10 have requested this problem solution
The more requests, the faster the answer.