Smooth leading edge transition in hypersonic flow | Zendy

Ludovic Le Gaillard | Zendy; Emmanuel Bénard | Zendy; T. Alziary de Roquefort | Zendy

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Smooth leading edge transition in hypersonic flow

Author(s) -

Ludovic Le Gaillard,

Emmanuel Bénard,

T. Alziary de Roquefort

Publication year - 1999

Publication title -

experiments in fluids

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 1.01

H-Index - 122

eISSN - 1432-1114

pISSN - 0723-4864

DOI - 10.1007/s003480050276

Subject(s) - mach number , hypersonic speed , boundary layer , mechanics , materials science , wind tunnel , heat flux , leading edge , cylinder , boiler blowdown , flow (mathematics) , hypersonic flight , hypersonic flow , flux (metallurgy) , hypersonic wind tunnel , stagnation temperature , stagnation point , optics , physics , heat transfer , geometry , geology , inlet , mathematics , geomorphology , metallurgy

The boundary layer transition along the attachment line of a smooth swept circular cylinder in hypersonic flow is investigated in a blowdown wind tunnel. A wide range of spanwise Mach numbers Me (3.28 to 6.78) is covered with the help of different models at several sweep angles (60 degrees less than or equal to Lambda less than or equal to 80 degrees). The transition is indirectly detected by means of heat flux measurements. The influence of the wall to stagnation temperature ratio is investigated by cooling the model with liquid nitrogen

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