高超声速摩擦阻力直接测量实验研究

Direct measurement of skin friction in hypersonic wind tunnel

介绍了在中国航天空气动力技术研究院(CAAA)的高超声速风洞FD-03和FD-07中进行的摩擦阻力直接测量实验。实验目的是测量高超声速流场中模型表面的摩擦阻力。研制了应变型两分量和单分量天平,分别应用这2种天平进行了压缩拐角运动实验和乘波体模型变迎角实验。实验中的总压1MPa,总温360K,马赫数5。每个模型各布置2个天平。在压缩拐角实验中,测量了平板区的摩擦阻力,观察到压缩拐角运动对流场的干扰,并测得了压缩拐角运动干扰区的摩擦阻力。在乘波体实验中测量了模型表面摩擦阻力及其与模型迎角的关系。实验的数据中处理引入温度修正。整体实验测量不确定度良好,优于12%。

The experiments of direct measurement of skin friction in hypersonic wind tunnels FD-03 and FD-07 of CAAA are introduced.Two-component and one-component strain-gage balances are developed to the application of moving compression ramp experiment and wave rider experiment,respectively.In the experiments,the total pressure is 1MPa,total temperature is360 Kand Mach number is 5.There are two balances installed in each model as measuring points.In the moving compression ramp experiment,the skin friction of plate is measured.The flow field is found to be interfered by the moving compression ramp,and the skin friction of the compressed ramp motion interference region is measured.In the wave rider experiment,the skin friction of the model is measured and the relationship between the skin friction and the angle of attack has been found.Temperature correction is introduced to the experimental data processing.In all the experiments,the uncertainty is less than 12%.