论文部分内容阅读
为了对通用航空飞行器(CAV)从近连续流到稀薄过渡流气动热特性进行研究,用红外热图技术在地面试验中测量了在典型轨道参数状态下CAV表面的热流分布。首先介绍了气动热试验研究所用的高超声速低密度风洞、红外热像仪等主要仪器设备的性能参数以及高超声速通用航空飞行器模型。其次介绍了高超声速低密度风洞气动热试验采用的3种模拟准则即粘性干扰参数、总焓与壁面焓差参数和克努曾数。最后,在马赫数M∞=7、12,攻角α=0°、12°、24°试验条件下,获得了CAV模型迎风面、背风面、侧面典型的流场结构图、红外热图和热流分布,并对CAV模型在不同状态下迎风中心线与翼前缘热流的试验结果、迎风中心线试验结果与工程计算结果进行了比较。研究表明:翼边缘热流大小呈现“马鞍形”分布,攻角变化对气动加热影响比较明显。
In order to study the aerodynamic characteristics of CAV from near-continuous flow to lean transitional flow, the heat flow distribution on the surface of CAV under typical orbital parameters was measured by using infrared thermography. Firstly, the performance parameters of hypersonic low-density wind tunnel, infrared thermal imager and other instruments and instruments as well as the hypersonic general aviation aircraft model used in the aerodynamic test are introduced. Secondly, the three kinds of simulation criteria used in the aerodynamic test of the hypersonic low-density wind tunnel are the viscous disturbance parameters, total enthalpy and enthalpy difference parameters and Knudsen number. Finally, under the experimental conditions of Mach number M∞ = 7,12, angle of attack α = 0 °, 12 °, 24 °, the flow field structure of the windward side, the leeward side and the side of the CAV model are obtained. The distribution of heat flow and the results of the test on the centerline of the upwind wind and the front of the wing under different states of the CAV model are compared with those from the engineering calculation. The results show that the size of wing edge heat flow presents a “saddle-shaped” distribution, and the change of angle of attack has a significant effect on aerodynamic heating.