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Design method with controllable velocity direction at throat for inward-turning inlets

Chinese Journal of Aeronautics 2019年第6期32卷 1403-1415页

作者： Wenyou QIAO Anyuan YU Wei GAO Weixing WANG Research Center of Combustion Aerodynamics Southwest University of Science and TechnologyMianyang 621010China Jiangsu Province Key Laboratory of Aerospace Power System Nanjing 210016China Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute China Aerodynamics Research and Development CenterMianyang 621000China College of Energy and Power Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China

In the design of a hypersonic inward-turning inlet by applying the traditional basic flowfield, a reflected shock-wave is formed in the isolator due to the continuous reflection of the cowlreflected shock wave in the basic flow-field, which interacts with the boundary layer to produce a considerable influence on the performance of the inlet. Here, a basic flow-field design method that can control the velocity direction at the throat section is developed, and numerical simulations are conducted to demonstrate the effectiveness of this method. The method presented in this paper can achieve the absorption of the reflected waves at the shoulder of the basic flow-field by adjusting the variation law of the center radius in the basic flow-field, and a smooth transition between the compression surface and the isolator can also be produced. The Mach number and total pressure recovery coefficient of the inlet designed according to this method are 3.00 and 0.657, respectively, at design point(the incoming flow Mach number Ma1= 6.0). The results show that with this method, the inlet can efficiently weaken both the reflection of the shock wave and the interaction between the boundary layer and the reflected shock waves, which improves the aerodynamic performance of the inlet.

关键词： Hypersonic Inverse design inward-turning inlet Method of characteristic Shock wave

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