Numerical Study on Unstart Phenomena due to Compound Choking of Scramjet Engine Inlets. (1st Report). Compound Choking of Inlets in a Shear Flow.

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  • スクラムジェットエンジンの複合閉塞による不始動遷移に関する数値解析　（第１報）　せん断流における複合閉塞
  • スクラム ジェット エンジン ノ フクゴウ ヘイソク ニ ヨル フ シドウ カ
  • Compound Choking of Inlets in a Shear Flow
  • 剪断流における複合閉塞

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Abstract

Unstart phenomena due to compound choking of airframe-integrated scramjet engine inlets were investigated numerically. The compound choking is a phenomenon caused by interaction between the main flow and the boundary layer flow ingested into engines. The numerical analysis was performed by using a one-dimensional two-stream-tube model and a quasi-three dimensional MacCormack differential model. The two-stream-tube model allowed to predict the choking condition at the throat from the given inlet conditions of stream tubes. The results of both analyses coincide qualitatively, and it is shown that the boundary layer flow spreads and pushes out the main flow in engine inlets, and that engines designed assuming a uniform inlet flow can be made unstart easily because of the existence of a low flow speed region like a boundary layer. When side walls of engines sweep backward, the transition from start to unstart is rather continuous and the inlet performance at unstart conditions is not so badly deteriorated as the performance of inlets without sweep.

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