A-11 超音速エンジン内部流における非一様流れと衝撃波の制御に関する研究(空力I,一般講演)

概要

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In scramjet engine duct with side-wall compression inlet, non-uniform flow field is known to appear due to the interaction between thick boundary layer from fore-body surface and the internal main flow as well as shock waves. The boundary layer may be separated in the duct. The non-uniform flow is accompanied with a low Mach number and low pressure region, and the region likely to enhance un-start transition of the engine since the low Mach number region acts as a communication path between isolator and combustor. In the present study, the three-dimensional supersonic flow field in the inlet and isolator duct of a supersonic engine was numerically simulated, and the generation mechanism of the non-uniform flow field was studied in detail. Effect of flow suction from body sidewall surface on the non-uniform flow field was numerically examined. The suction effect on un-start transition was also experimentally studied, and favorable effect was revealed.
公益社団法人日本ガスタービン学会の論文
2006-10-01