Experimental method study on heat flux measurement on sharp leading edge

The heat-flux measurement is the precondition of the structure and cooling system design for hypersonic aircraft, while no experiment method can be applied to the heat-flux measurement of the sharp leading edge for its small size and high-heat flux. In this article, an experimental method based on the law of inverse conduction is proposed in this paper for the calculation of heat flux from the inner wall temperature of the sharp leading edge. This experimental method proposed includes the method of inner wall transient temperature acquisition, smoothing technique, and the Matlab and Fluent cosimulation postprocessor, where Fluent is used as a 3D unsteady heat conduction solver, and conjugate gradient method is applied for optimization. The effectiveness of the proposed method is verified by its application in the scramjet experiment for the heat-flux measurement on the strut-leading edge, which greatly helps the assessment of thermal environment with a total error of less than 5%.