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本研究之目的是为了模拟可控有升力飞行器周围的加热和压力场,研究受热表面的烧蚀现象,以便发展地面的实验能力。在电弧加热器上,利用超声速湍流平板技术,进行控制翼模型分离、传热和烧蚀实验。结果表明,由于翼角前有一条横缝,分离效应减弱,导致产生分离的最小翼角增大。由于分离流动影响,在翼上及其周围压力和热流升高,烧蚀速度大大增加。本文给出了有关的相关公式。
The purpose of this study was to simulate the heating and pressure fields around a controlled lift vehicle and to investigate the ablation of heated surfaces in order to develop the experimental capability of the ground. On the arc heater, the supersonic turbulent plate technique was used to control wing model separation, heat transfer and ablation experiments. The results show that due to the presence of a transverse slit in the corner, the separation effect is weakened, leading to the increase of minimum wing angle. Due to the influence of the separation flow, the pressure and heat flow on and around the wing are increased, and the ablation speed is greatly increased. This article gives the relevant formula.