Experiments in Fluids

, Volume 26, Issue 1, pp 169–176

Smooth leading edge transition in hypersonic flow

  • L. Gaillard
  • E. Benard
  • T. Alziary de Roquefort

DOI: 10.1007/s003480050276

Cite this article as:
Gaillard, L., Benard, E. & Alziary de Roquefort, T. Experiments in Fluids (1999) 26: 169. doi:10.1007/s003480050276

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.

Copyright information

© Springer-Verlag Berlin Heidelberg 1999

Authors and Affiliations

  • L. Gaillard
    • 1
  • E. Benard
    • 1
  • T. Alziary de Roquefort
    • 1
  1. 1.Laboratoire d’Etudes Aérodynamiques UMR6609, CEAT, 43 Route de l’Aérodrome, F-86036 Poitiers cedex, FranceFR