Abstract
Scramjet engine performance mainly depends on the establishment of supersonic flow in the air intake. The air intake geometry plays a dominant role in obtaining the required pressure recovery of the intake; thereby influencing the performance of the combustion chamber. This study is the numerical simulation of a scramjet inlet at Mach number of 6, in order to study the performance characteristics of the inlet at various angles of attack (AOA). The scramjet inlet used here is a mixed compression type with two external ramps. Inlet characteristics and the effect of fuel injection strut blockage on the performance of the inlet are studied. For the strut blockage of 20 % and at zero angle of attack, the pressure recovery of the inlet is found to be about 21 % and the inlet is in started condition. It is found that the pressure recovery decreases as the angle of attack increases for a fixed strut blockage which results in much spillage of air.
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