Smooth leading edge transition in hypersonic flow
- Cite this article as:
- Gaillard, L., Benard, E. & Alziary de Roquefort, T. Experiments in Fluids (1999) 26: 169. doi:10.1007/s003480050276
- 63 Downloads
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.