Pressure distribution induced by the interaction between the shock wave and the turbulent boundary layer around a compression corner = 모퉁이 초음속 난류 흐름에서 경계층과 충격파의 상호작용에서 유도된 압력분포의 이론적 해석

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The pressure distribution induced in the interaction between the shock wave and the unseparated supersonic turbulent boundary layer at a compression corner is considered, with the Mach number of the undisturbed external flow lower than five. The method of asymptotic expansions is used, with solutions valid in the double limits as Reynolds number tends to infinity and the corner angle is much smaller than unity. The undisturbed boundary layer is characterized by the law of the wall in the wall layer and the law of the wake in the velocity defect layer for the compressible flow. It is shown that the induced pressure distribution can be calculated only in the velocity defect layer without considering the wall layer and is independent of the closure condition. In the case of a supersonic turbulent boundary layer with no separation, the sonic line is so close to the wall that the upstream influence is very small. The analysis of the pressure consists of two parts; the outer solution of the defect layer which covers most interaction region except the small region around the shock root and the inner solution of the defect layer which explains the upstream influence near the shock root.
Advisors
Chang, Paul K.장극
Description
한국과학기술원 : 항공공학과,
Publisher
한국과학기술원
Issue Date
1984
Identifier
64001/325007 / 000821008
Language
eng
Description

학위논문(석사) - 한국과학기술원 : 항공공학과, 1984.8, [ [vii], 62 p. ]

URI
http://hdl.handle.net/10203/26590
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=64001&flag=dissertation
Appears in Collection
AE-Theses_Master(석사논문)
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