Abstract：A computation program was developed based on Method of Characteristic (MOC), with which the supersonic inlet compression surface was designed according to the prescribed parameter change law along the compression surface. The influence of pressure gradient and Mach number gradient on inlet performance was studied and compression surface was designed overall considering the two laws of compression. It was showed that efficiency of the design of supersonic inlet compression surface was greatly increased with the use of the MOC method. Strategy design was conducted, through which the compression surface with high capability was obtained. The pressure gradient in the rear section was greatly decreased and the outlet parameter distribution was more even if the compression law of Mach number cubic curve was adopted, the pressure gradient would also be reduced and better compression results would be gained.
杨帆, 李小林, 刘小波, 傅建明. 基于特征线理论的超声速进气道压缩面设计研究[J]. 空天防御, 2019, 2(1): 22-28.
YANG Fan, LI Xiaolin, LIU Xiaobo, FU Jianming. Investigation on the Supersonic Inlet Compression Surface Design Based on the MOC Method. Air & Space Defense, 2019, 2(1): 22-28.
