Abstract

The results of numerical simulation of experimental data on the thermal and force effects on the experimental hypersonic aircraft HIFiRE-1 at flight speeds of M = 6.58 and 7.16 are presented. The calculations were made using the author’s computer code, which implements the finite-difference technology for integrating the set of Reynolds-averaged Navier–Stokes equations on multiblock structured grids using two algebraic turbulence models. Taking into account the laminar–turbulent transition and the turbulent nature of the flow near the aft skirt of the HIFiRE-1 aircraft makes it possible to obtain good agreement with the experimental data.

中文翻译：

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高超声速飞机HIFiRE-1空气热力学实验数据的计算分析

摘要

给出了在M = 6.58和7.16的飞行速度下对实验性高超音速飞机HIFiRE-1的热力作用力的实验数据的数值模拟结果。计算是使用作者的计算机代码完成的，该计算机代码实现了有限差分技术，该技术使用两个代数湍流模型将雷诺平均Navier-Stokes方程组集成到多块结构化网格上。考虑到层流-湍流过渡以及HIFiRE-1飞机后裙部附近流动的湍流特性，可以与实验数据取得很好的一致性。