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应用数值模拟技术,采用“模拟前机身”的方法,把模拟对象按某种规律在长度方向上缩短1/2后,可将模拟流场与基准流场间的参数差控制在10％左右,吸除边界层后,可直接使用三维Euler法来判断机身缩短后的影响,而不必求解雷诺平均薄层N-S方程组。理论研究业已证明,用此方法,可在较小尺寸的自由射流式超音速风洞中开展带有飞机前部纵面的进气道/前机身组合大模型的实验研究,从而解决了进/发匹配课题中的一大技术关键。
Applying the numerical simulation technology, using the method of “simulating the front fuselage”, the simulation object can be shortened by 1/2 in the length direction according to a certain rule, and the parameter difference between the simulation flow field and the reference flow field can be controlled at about 10% After suctioning the boundary layer, the 3D Euler method can be directly used to judge the effect of shortening of the fuselage without having to solve the Reynolds-averaged sheet NS equations. Theoretical studies have demonstrated that using this method, an experimental study of the inlet / front fuselage composite model with the front of the aircraft can be carried out in a smaller size free-jet supersonic wind tunnel One of the major technical issues in matching topics.