COMPUTATIONAL ANALYSIS OF HYPERSONIC COMBUSTOR USING STRUT INJECTOR AT FLIGHT MACH 7

Numerical analysis of the hypersonic combustion and flow structure through a scramjet engine at a flight Mach 7 with parallel fuel injection at different angles of attack, alpha = (-5 degrees), 0 degrees, and 5 degrees have been studied in the present research article. The scramjet configuration incorporates an inlet angle of 8 degrees compression ramp followed by an insulator and a divergent combustor for parallel injection. The shape of the strut is chosen such that it produces strong stream-wise vorticity and thus enhances the air/fuel mixing. These numerical simulations were aimed to study the flow structure, supersonic mixing, and combustion efficiency. For parallel injection investigation, the influence of the strut injector and the variation of angle of attack on the flow behavior in reacting cases have been studied. The shock structure and combustion phenomenon are affected by the combustor geometry, flight Mach number, and by the trajectory.