Double Inverse Design Of 2-D Hypersonic Inlet With Controllable Exit Mach Number Distribution

The relative mature hypersonic inlets design methods are forward design at present. But forward design cannot give good consideration to the combustor/isolation’s requirements of incoming flow, which will decrease the performance of scramjet. Therefore, realizing the inlets inverse design base on the controllable exit mach distribution becomes especially important. The contemporary inverse design research at home and abroad focus on the problem that inverse compute wall through the known wall condition mostly, and few works have been done to realize the controllable exit mach distribution. Based on the theory of two-dimensional rotational characteristics and the technology of streamline tracing and flow field assembling, the paper explored the double inverse design method that the mach number distribution of wall and exit is controllable simultaneously.The paper continued to research the inverse design with two curved shock waves to control exit mach number distribution. In order to improve the performance of inlet and realize the ratio of shock compression and isentropic compression are controllable flexibly, and also flexible adjust the flow parameters of assembly point, the paper explored a two curved shock waves double inverse design method with the mach number distribution of rear compression surface is controllable. The results show that the double inverse design method not only can flexible adjust the ratio of shock compression and isentropic compression, but also reduce the contraction radio and shoulder flow separation.Secondly, because of the inlet total pressure comes mainly from shock loss, in order to improve performance further, so that the inverse design can be closer to the practice, the paper explored the three curved shock waves double inverse methods base on the two curved shock waves method. The numerical results show that the three curved shock waves double inverse methods can realize the desirable exit mach profile under the incoming flow condition is uniform or non-uniform. The exit mainstream mach distribution fits the given target well after viscosity correction. The uniformity of exit can keep within certain incoming mach number range.Finally, the two kinds of inverse design methods were compared. Under the design condition of the paper, with the same capture height, inviscid exit height, design inviscid total pressure recovery coefficient and assembly point’s flow parameters, the results of two-dimensional numerical simulation show that the two curved shock waves method has the advantage of simple wave system and higher flow coefficient under the incoming flow condition of Ma4, and the three curved shock waves method has the advantage of smaller contraction radio and higher total pressure recovery coefficient at both design and off-design point. The results of three-dimensional numerical simulation show that the three curved shock waves method also has the advantage of smaller exit vortex area, ruler exit mainstream area and less exit total pressure distortion.