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Unstructured Euler solutions for missile aerodynamics

机译：导弹空气动力学的非结构Euler解

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摘要

The purpose of this paper is to validate an unstructured 3D Euler flow solver, USER3D, against the experimental data and to compare it with a classical, structured, Euler solver, FLU3M of ONERA, on two different missile geometries at a Mach number of 2 and at various angles of attack up to 20°. The firs geometry is a conventional missile with an give nose, a cylindrical body and four straight tail fins. The second geometry is a unconventional missile with a lenticular body and no tail fins. The present results are found to be in good agreement with these available results and he discrepancies observed between them are explained in detail. The present unstructured Euler code has proved to be accurate, fast, and reliable for he aerodynamic design of Conventional and unconventional missiles.
机译：本文的目的是针对实验数据验证非结构化3D Euler流动求解器USER3D，并将其与经典的结构化Euler求解器FERA3M（ONERA）进行比较，以两种不同的马赫数分别为2和3的导弹几何形状进行求解。在高达20°的各种迎角下冷杉的几何形状是一种常规的导弹，带有一个鼻翼，一个圆柱体和四个直尾鳍。第二种几何形状是非常规导弹，具有双凸透镜体，没有尾鳍。发现本结果与这些可获得的结果高度吻合，并详细解释了它们之间观察到的差异。对于常规和非常规导弹的空气动力学设计，目前的非结构化Euler编码已被证明是准确，快速和可靠的。

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