Broad-speed-range wing design of supersonic civil aircraft based on engineering

In addition to ensuring the aerodynamic performance of supersonic flight,the aerodynamic design of supersonic civil aircraft needs to satisfy the low speed characteristics required by the project. Especially,attention should be paid to the pitching torque elevation angle and aileron efficiency characteristics at low speed. The CFD numerical method based on Reynolds average Navier-Stokes equation is used to calculate the full velocity aerodynamic characteristics of a typical low-boom supersonic civil aircraft configuration. The reasons for the lack of pitching moment elevation and aileron efficiency are analyzed. The influence of leading-edge radius,leading-edge sagging position and swept angle on the matching of high/low-velocity aerodynamic characteristics is studied. It was evaluated that the optimal scheme had good aerodynamic performance at Ma=1. 8 with a lift-to-drag ratio of 8. 28. At the same time,when Ma=0. 3,the elevation angle of the pitching moment was delayed to 14°,and the efficiency of aileron remained above 80% within the calculated angle of attack. The aerodynamic design scheme of wide-speed-range airfoil satisfying engineering requirements is proposed. It is practical to solve the problem of matching high/low-speed aerodynamic characteristics of supersonic civil aircraft.