壁面形状对混压式轴对称进气道波系及气动性能影响研究

A mixed-compression axisymmetric inlet with cruise Ma=1.8 is designed. The causes of 'λ' wave，shoulder shock wave and secondary shock waves in the inlet are analyzed. The effects of wall shape changes on the aerodynamic performance of the inlet，such as wave structure，anti-backpressure ability and total pressure recovery coefficient，are studied. The results show that the formation of 'λ' wave and shoulder shock wave in the inlet is due to the shock wave boundary layer interference near the wall of the lip cover and the design of the shoulder chamfer. With the decrease of D（shoulder chamfer radius / throat height），the area occupied by the 'λ' wave gradually decreases，and the number of acceleration zones near the shoulder shock wave decreases. The shape of the lip cover changes the size of the low-energy fluid area at the lip cover，which has little effect on the 'λ' wave and shoulder shock wave structure. When PR（pressure ratio）is 4.5，there is a secondary shock wave at the throat of the inlet. When D increases from 0.61 to 1.22，the length of the secondary shock wave increases by 11.58%. When the shoulder chamfer radius is different，the anti-backpressure ability of the inlet is different. When D increases from 0.61 to 1.22，the critical pressure ratio of the inlet increases from 4.19 to 4.63，and the total pressure recovery coefficient of the throat also increases.