激波风洞高超声速摩阻直接测量技术研究

介绍了在中国空气动力研究与发展中心（CARDC）激波风洞中进行的摩阻测量技术研究情况。在测量研究中，设计了压电型摩阻天平，为了提高摩阻天平的校准和风洞试验测量结果精度，便于风洞试验和校准之间安装的变换，本项研究的摩阻天平采用一种新结构，也就是测量表面和摩阻天平本体可以分离的分体式结构，由此确保在不同使用场合下，摩阻天平的测量表面或者校准加载块可拆卸和更换。验证性试验是在CARDC0．6m激波风洞中进行的，流场名义马赫数分别为8和10，单位雷诺数分别为2．85×10^7／m和1．58×10^7／m，试验中测量了带压缩拐角的进气道模型表面三个测点的摩擦阻力，也测量了摩阻测点及其附近热流，测量结果表明：模型表面的摩阻和热流与雷诺比拟准则符合得较好。

Direct measurement of skin friction at hypersonic shock tunnel

The research of direct measurement of skin friction in hypersonic shock tunnel is in troduced in this paper. In the study, the piezoelectric skin friction balance was developed to test the skin friction of the model of engine inlet with compressed corner. In order to improve the pre- cision of calibration and experiment result, and easy to change between the calibration and wind tunnel experiment, a new skin friction balance structure was used. In this new structure, the skin friction balance has a separated measurement head with balance main body, which will en- sure the measurement head and calibration head could he changed in different situations, The measurements were conducted in the flow field with the nominal mach number of 8 and 10, Reyn- olds number of 2.85×107/m and 1.58× 107/m in 40.6m shock tunnel of CARDC. The heat flux near the skin friction test location was tested using platinum thin film sensors, the results are co- incided with the Reynolds analogy.