Experimental method study on heat flux measurement on sharp leading edge

Abstract

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 highheat 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%.

Investigation of Heat Loads onto an Internally Cooled Strut Injector for Scramjet Application

“…Detailed numerical and experimental investigations of heat fluxes on strut leading edges have been conducted recently, 8,9 which highlight the increased heat loads in this region of the injector. As most of the available materials can not withstand the extreme stagnation temperatures, an internal cooling mechanism is needed to preserve the structural integrity especially of the leading edge.…”

Investigation of aerodynamic heating in V-shaped cowl-lip of the inward turning inlet

“…There are a number of aerodynamic heating studies on the leading edge. However, most of the research is mainly focused on heat flux of the aircraft nose 17–21 and the cowl-lip of other configuration inlets. 22–24 Lu et al.…”

“…There are a number of aerodynamic heating studies on the leading edge. However, most of the research is mainly focused on heat flux of the aircraft nose [17][18][19][20][21] and the cowl-lip of other configuration inlets. [22][23][24] Lu et al 25 studied four cowl-lip blunting methods and the corresponding flow characteristics and performances of the generic hypersonic inlets.…”