Design Method and Performance of Constant Surface Pressure Gradient Compression System

摘要：

Based on the oblique shock and expansion wave theory, at the design point inflow condition, assuming that constant pressure gradient along the surface, the shapes of needed surface and its shock wave are defined. Changed the inflow conditions, the other shapes of shock wave can be obtained. Comparison the results of numerical analysis with the calculating results with Fluent software, they showed that the numerical analysis method is feasible. Under the wind tunnel experimental conditions of inflow Ma5.3 and Ma3.85, studying the performance of the curved compression system under the uniform and non-uniform incoming flow conditions, the results show that: in the uniform incoming flow conditions, both design point and non-design point, the pressure gradient distribution along the surface of compression system is constant. The shapes of shock wave are good agreement with the numerical simulation results; under the uniform and non-uniform incoming flow conditions, the pressure gradient distribution along curved compression system is still nearly constant, these are good for preventing boundary layer separation.

关键词： curved compression surface nonuniform inflow supersonic wind tunnel

作者: Jin Pan Kun-yuan Zhang

作者单位: College of energy and power engineering, Nanjing University of Aeronautics and Astronautics Nanjing, Jiangsu, 210016, China

会议类型: 国际会议

会议名称: The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)

会议地点: 南京

会议语种:英文

页码: 244-248

在线出版日期: 2010-09-13（万方平台首次上网日期，不代表论文的发表时间）