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本文给出了在跨音速流动中,计算三维机翼非定常载荷分布的核函数法和计算结果。此方法是基于线化升力面理论,利用在亚、超音速情况下,联系载荷分布与下洗的积分方程的核函数,采用局部线化法来处理跨音速的非定常绕流问题。在计算中引进了线分布的冲波偶极子,并嵌入适当的正冲波边界条件。 我们从统一的超、亚音速核函数表达式出发,对亚音速区数值积分作了新的简便的处理,对于亚、超音速区相互的诱导下洗给出了自己的数值积分过程。我们算了三个例题,和文献上的数值符合较好。
This paper presents the kernel function method and calculation results for the calculation of the unsteady load distribution of the three-dimensional wing in transonic flow. This method is based on the theory of linearized lifting surface, and utilizes the kernel function of the integral equation of load distribution and washdown under sub-supersonic conditions. The local linearisation method is used to deal with the unsteady transonic flow around the flow. The calculation of the introduction of the line distribution of the dipole dipoles, and embedded in the appropriate positive boundary conditions. Based on the unified super subsonic and subsonic nuclear function expressions, we have made a new and simple numerical treatment of the subsonic subspace, and have given our numerical integration process for the sub-supersonic velocities. We have calculated three examples, which are in good agreement with the literature.