Smooth leading edge transition in hypersonic flow |
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| Authors: | L Gaillard E Benard T Alziary de Roquefort |
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| Institution: | (1) Laboratoire d’Etudes Aérodynamiques UMR6609, CEAT, 43 Route de l’Aérodrome, F-86036 Poitiers cedex, France, FR |
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| Abstract: | 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°?Λ?80°). 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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