Abstract:
In the take-off stage, especially around the zero-velocity-state of aircrafts, supersonic inlets have a poor performance. Specifically, the total pressure recovery coefficient at the inlet exit is small and the total pressure distortion coefficient is large, which has a negative effect on the efficient and stable operation of aero-engines. Consequently, the inlet-engine matching during the take-off is one of the key problems that has received substantial attention. In this paper, experiments and numerical simulations by Computational Fluid Dynamics are used to study the matching between a two-dimensional supersonic inlet and an aero-engine. Flowfield structures in the inlet as well as the variation of total pressure recovery coefficient and total pressure distortion coefficient with the engine speed are analyzed. Results suggest that removing the protective net helps improve the performance of the inlet, which is further verified by an experiment of a full-size inlet and engine. Moreover, in view of the difference between the test conditions and real flight conditions, numerical analyses are performed to provide a basis for the extension of test results to flight conditions.