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Effect of steps and gaps on aerothermodynamics for the IXV hypersonic vehicle

机译：台阶和间隙对IXV高超音速飞行器空气热力学的影响

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摘要

The general aerothermodynamics environment of hypersonic vehicles is usually performed considering a smooth simplified geometry. However, in the case of the intermediate experimental vehicle (IXV), the thermal protection system includes a mono-block ceramic matrix composite nose and an assembly of shingles between which steps and gaps are generated. From an aerothermodynamic point of view, such a distributed roughness layout cannot be ignored in terms of modification of the interaction between the flow and the body and possible induced transition along the windward side. To assess these effects, dedicated wind tunnel tests and numerical simulations have been performed. This paper presents the general logic of the work, with emphasis on the wind tunnel model design, tests involving infrared thermal measurements as well as the computational fluid dynamics (CFD) rebuilding of the flow in the wind tunnel and the extrapolation from ground to flight.
机译：高超声速飞行器的一般空气动力学环境通常是在考虑平滑简化几何形状的情况下执行的。但是，在中间实验车辆（IXV）的情况下，热保护系统包括一个整体式陶瓷基质复合材料机头和一个带状板组件，在它们之间会产生台阶和间隙。从空气动力学的角度来看，这种分布的粗糙度布局在流与主体之间的相互作用的修改以及沿上风侧可能引起的过渡方面不能忽略。为了评估这些影响，已经进行了专用的风洞测试和数值模拟。本文介绍了工作的一般逻辑，重点是风洞模型设计，涉及红外热测量的测试以及风洞中流动的计算流体力学（CFD）重建以及从地面到飞行的推断。

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