论文部分内容阅读
高超声速气动力试验模拟准则的有效性问题阻碍了飞行器气动性能预测能力的发展。鉴于此,将尺度化方法应用于实验空气动力学领域,基于连续流域高超声速流动的双尺度特点,对各参数选取适当的尺度将流动控制方程尺度化。针对典型飞行状态,通过计算尺度化方程中各系数的量级,获取高超声速气动力试验模拟参数的选择准则。研究表明:建立的模拟参数选取方法为现有的高超声速气动力试验模拟准则提供了理论支持,模拟参数的选取准则随飞行条件发生显著改变。应用理论分析方法验证了黏性干扰参数是高马赫数高超声速气动力试验中的重要模拟参数,并与国外关于黏性干扰效应关联区域的结论进行了相互验证。
The validity of the hypersonic aerodynamic test simulation criterion hinders the development of the aircraft aerodynamic performance prediction ability. In view of this, the scaling method is applied in the field of experimental aerodynamics. Based on the double-scale characteristic of hypersonic flows in continuous watershed, the flow control equation is scaled to the appropriate scale for each parameter. According to the typical flight condition, the selection criterion of hypersonic aerodynamic test simulation parameters is obtained by calculating the magnitude of each coefficient in the scaling equation. The research shows that the established method of selecting simulation parameters provides theoretical support for the existing hypersonic aerodynamic test simulation criteria, and the selection criteria of simulation parameters change significantly with the flight conditions. Theoretical analysis method is used to verify that viscous interference parameter is an important simulation parameter in hypersonic aerodynamic test with high Mach number, and the conclusion is verified with the conclusion of foreign related region of viscous interference effect.