Investigation of Supersonic Combustor Full Flowfield at Actual Combustor Inlet Conditions

Aiming at self-designed scramjet inlet / isolator + combustor integrated model,this paper carried through cold experimental and numerical investigation of supersonic combustor full flowfield under the conditions of the supersonic stream.The flow structure and the static pressure distribution along the airflow of the model under different stream total pressure and exit backpressure has been obtained.The test actually simulated the cold conditions of the entrance environment of the combustor.And the results showed that when the coefficient of the backpressure was lower,the shock train formed near the expansion section of the combustor,By contrast,when the coefficient of the backpressure was higher,the shock train formed in the combustor entrance,and the shock train was squeezed to the top wall of the combustor because of the cavity.