Abstract: local wall shear stress on hypersonic vehicles during actual flight is challenging due to the harsh aerodynamic envi-ronment. To address this, a novel differential pressure-based sensor has been designed for local wall shear stress measurement on hypersonic flat plates. The sensor utilizes two neighboring static pressure holes with dissimilar diameters or inclination angles. Wall shear stress creates vortex structures within these holes, effectively transforming changes in fluid momentum into variations in pressure difference. This test technology offers reliable measurement of local wall shear stress in hypersonic boundary layers due to its minimal interference and high reliability. Given the complexities arising from hypersonic gas compressibility, a com-bined experimental and numerical methodology is employed to study this test technology. The effects of static pressure hole diameter, inclination angle, and inflow azimuth on the test results are analyzed. The static pressure hole pair, consisting of a vertical and an inclined hole, exhibits maximum sensitivity at a 0° azimuth angle, with excellent linearity between sensor output pressure difference and local wall shear stress. The influence of the static pressure hole pair layout on sensor performance is also investigated.