Abstract: 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.