대한기계학회논문집 (Transactions of the Korean Society of Mechanical Engineers)
- 제19권9호
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- Pages.2283-2296
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- 1995
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- 1225-5963(pISSN)
DOI QR Code
초음속디퓨져에서 발생하는 수직충격파의 난류경계층의 간섭에 관한 실험
A New Experiment on Interaction of Normal Shock Wave and Turbulent Boundary Layer in a Supersonic Diffuser
초록
Experiments of normal shock wave/turbulent boundary layer interaction were conducted in a supersonic diffuser. The flow Mach number just upstream of the normal shock wave was in the range of 1.10 to 1.70 and Reynolds number based upon the turbulent boundary layer thickness was varied in the range of 2.2*10
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