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Smooth leading edge transition in hypersonic flow

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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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Authors and Affiliations

  1. Laboratoire d’Etudes Aérodynamiques UMR6609, CEAT, 43 Route de l’Aérodrome, F-86036 Poitiers cedex, France, , , , , , FR

    L. Gaillard, E. Benard & T. Alziary de Roquefort

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  1. L. Gaillard
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  2. E. Benard
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  3. T. Alziary de Roquefort
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Received: 19 January 1998/Accepted: 10 May 1998

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Gaillard, L., Benard, E. & Alziary de Roquefort, T. Smooth leading edge transition in hypersonic flow. Experiments in Fluids 26, 169–176 (1999). https://doi.org/10.1007/s003480050276

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  • DOI: https://doi.org/10.1007/s003480050276

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