兼顾后体效应的乘波翼身融合布局设计方法及数值模拟研究

Aiming at the design requirements of future hypersonic aircraft, this study proposes a wide-speed range aerodynamic design method that integrates waverider forebody-wing topological coupling while considering aft-body effects. Based on utilizing vortex lift and shockwave compression, this approach enhances the vehicle’s aerodynamic widespeed range performance by suppressing pressure leakage from strake wings and trailing edge flow separation. First, base configuration is established by generating forebody waverider and multiple wide-speed range optimized airfoils. Second, aft-body topological design is conducted through determining aft-body length using characteristic lines and shock angle, coupled with constructing symmetrical plane geometry through assembling multiple parametric curves. Subsequently, three-dimensional configuration coupling is achieved by inputting forebody geometric parameters and transonic constraints into the osculating-cone method. Finally, optimized airfoils are integrated to form a new three-dimensional waverider blended wing body configuration. Numerical simulations demonstrate that compared with conventional waverider-wing configurations, the new layout achieves 45. 6% lift coefficient improvement at Ma 0.4, 8. 6% drag coefficient reduction at Ma 1, and 15. 8% lift-to-drag ratio improvement at Ma 5, while effectively suppressing hypersonic pressure leakage and maintaining favorable aerodynamic characteristics within specific angles and speed ranges, validating the effectiveness of the proposed design method.