关键词: 机翼, 可压缩边界层, 层流, 湍流, 积分方程, 数值计算

Abstract: Based on three-dimensional, time-dependent momentum and mean-flow kinetic energy integral equations for compressible boundary Layers in nonorthogonal curvilinear coordinates, the existing algorithm for two-dimensional, compressible, Laminal and turbulent integral equations is extended to solve the boundary-layer problem over finite swept wings. The equations are solved by using the four-step Runge-Kutta Scheme with local time marching to accelerate the convergence. The stability and convergence of the numerical scheme is analyzed, and the effect of the crossflow dissipation integral upon the calculation are examined. Numerical results of steady, compressible, laminal and turbulent boundary layers over the finite swept wing show to be satisfactory.

Key words: Wings, Comysressible boundary layers, laminar flow, turbulant flow, integral equations, numerical calculation