跨速域大后掠角近距耦合翼气动干扰特性

The paper investigates the aerodynamic interference of close-coupled highly swept-back wings to the tail wings at transonic velocity which is from subsonic velocity to hypersonic velocity. The numerical method is based on the Reynolds-averaged Navier-Stokes equations and finite volume method. The Spalart-Allmaras turbulence model is used to simulate the flow field around an air vehicle with close-coupled highly swept-back wings. The distributions of aerodynamic coefficients of tail at different Mach numbers and angles of attack under the influence of the front wing are given. The variation of surface pressure coefficient and the flow structure of tail are analyzed to figure out the aerodynamic interference mechanism. The results indicate that the flow field around tail is influenced greatly by the vortex from the highly swept-back wing under both subsonic and transonic flow conditions. The decrease in the pressure difference of upper and lower tail surfaces results in decreasing the lift coefficient and drag coefficient of tail. Besides, the greater the angle of attack is, the greater the vortex intensity is, and the greater the reductions of lift coefficient and drag coefficient of tail are. The influence of wing on tail decreases with the increase in Mach number.