超声速湍流流动中平板-楔模型分离、传热和烧蚀试验研究

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。

EXPERIMENTAL RESEARCH OF FLOW SEPARASION, HEAT TRANSFER AND ABLATION ON FLAT PLATE-WEDGES IN SUPERSONIC,TURBULENT FLOW

The purpose of the present study was to develop a ground test capability for simulating heating and pressure fields around the control wing of controllable lifting vehicles in order to study ablation phenomena on heatshield surfaces. In this paper, an experimental method based on an arc heater is introduced, and mojor results are shown for flow separation, heat transfer and ablation on a model of a control wing for supersonic, turbulent flow over a flat plate. The results obtained showed that with a transverse seam in front of wing angle, the effects of flow separation were weakened, hence lead to the minimum wing angle that produced flow separation increased. Because of the effects of flow separation, the pressures and heat fluxes raise, and the ablation velocities increase significantly in regions on and around the wing. This paper presents correlating formulas.