A Study of Aerothermal Loads in the Presence of Edney Type IV Interaction

L. Gurov, A. Ivanov
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Abstract

Numerical simulation results of specific supersonic and hypersonic flows interactions leading to complex shocks structures are presented in the paper. These interactions can produce abnormal thermal loads that should be taken into account for Thermal Protection System design for hypersonic vehicles. Calculations were made with the aid of CAD-Embedded CFD software FloEFD. To validate the CFD code in this field a study of shock/shock interaction near 2D cylinder has been carried out. Good agreement with experimental data in terms of shock structure, surface pressure and surface heat flux distributions was obtained. To demonstrate how these shocks interactions effects can affect in case of a real 3D complex hypersonic vehicle a 3D study of interaction between the Space Shuttle Orbiter bow shock and External Tank bow shock under certain flow regime has been carried out. Comparison with the data obtained in the simulation of the ‘single Orbiter’ flow showed a small-scale zone on Orbiter nose with considerably increased peak pressure and heat flux values due shock/shock interaction.
Edney IV型相互作用下的气动热载荷研究
本文给出了特定超声速和高超声速流动相互作用导致复杂激波结构的数值模拟结果。这些相互作用会产生异常热负荷,在高超声速飞行器的热防护系统设计中应予以考虑。利用嵌入式cad CFD软件FloEFD进行计算。为了验证该领域的CFD代码,对二维圆柱体附近的冲击/冲击相互作用进行了研究。在激波结构、表面压力和表面热流密度分布等方面与实验数据吻合较好。为了演示这些激波相互作用对实际三维复杂高超声速飞行器的影响,对航天飞机轨道飞行器艏激波与外油箱艏激波在一定流型下的相互作用进行了三维研究。与“单轨道飞行器”流动模拟数据的比较表明,由于激波/激波相互作用,轨道飞行器机头上有一个小范围的区域,峰值压力和热通量值显著增加。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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