CAJ | 학술논문

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 CARDC 0．6m 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2．85×107/m 和1．58×107/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。
개소료재중국공기동력연구여발전중심（CARDC）격파풍동중진행적마조측량기술연구정황。재측량연구중，설계료압전형마조천평，위료제고마조천평적교준화풍동시험측량결과정도，편우풍동시험화교준지간안장적변환，본항연구적마조천평채용일충신결구，야취시측량표면화마조천평본체가이분리적분체식결구，유차학보재불동사용장합하，마조천평적측량표면혹자교준가재괴가탁사화경환。험증성시험시재 CARDC 0．6m 격파풍동중진행적，류장명의마혁수분별위8화10，단위뢰낙수분별위2．85×107/m 화1．58×107/m，시험중측량료대압축괴각적진기도모형표면삼개측점적마찰조력，야측량료마조측점급기부근열류，측량결과표명：모형표면적마조화열류여뢰낙비의준칙부합득교호。
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 be 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 2.85×10 7/m and 1.58×10 7/m in0.6m 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.