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本文应用跨音速、定常、小扰动势流的混合差分方法,计算了机翼—挂架—外挂物气动力干扰。利用线超松弛改进迭代方法,在物理空间网格点上满足x向大扰动速势方程,在物面上满足精确的边界条件,在涡面上满足库塔条件,远场处取速势方程的线性解。计算网格点上的速势值ψ、下洗速度ψ_y、侧洗速度ψ_z:的分布,以及所有部件、组合体的压强分布、气动力系数,及机翼、外挂物各自所受的气动干扰量。 本程序用BCY语言在上海华东计算技术研究所655机上进行计算。文内三个算例均得到收敛或接近收敛的结果。与可以找到的风洞实验比较尚一致。
In this paper, the hybrid differential method of transonic, steady and small perturbed potential flow is used to calculate the aerodynamic interference of wing-pylon-plug. Using the method of line over relaxation to improve the iteration method, the large-disturbance x-direction velocity equation is satisfied on the grid point of the physical space, the boundary conditions are satisfied on the object surface and the kurtosis conditions are satisfied on the vortex surface. Linear solution. The distribution of the velocity value ψ, the wash rate ψ_y, the side wash velocity ψ_z: and the pressure distribution of all components and assemblies, the aerodynamic coefficient and the aerodynamic interference the amount. The program using BCY language in Shanghai East China Institute of Computing 655 machine calculations. The three cases in the paper all converge or close to the result of convergence. It is still in agreement with the wind tunnel experiment that can be found.