An experimental study of boundary layer transition on a slender cone at Mach 5
Abstract
Experimental results of an investigation conducted in a Ludwieg tube wind tunnel are presented. Transition was detected by means of local heat transfer rate measurements, and transition behavior on a 5 deg half-angle cone was investigated for different unit Reynolds numbers, temperature ratios and different angles of attack. In a range of unit Reynolds numbers from U/v = 100,000 to 5 x 100,000 transition Reynolds numbers were independent of unit Reynolds number. A variation of the wall to stagnation temperature ratio had no effect on transition. Small variations of angle of attack strongly affected transition, such that transition was promoted on the leeward surface and delayed on the windward surface.
- Publication:
-
In AGARD Laminar-Turbulent Transition 12 p (SEE N78-14316 05-34
- Pub Date:
- October 1977
- Bibcode:
- 1977ltt..agarQ....K
- Keywords:
-
- Angle Of Attack;
- Boundary Layer Transition;
- Reynolds Number;
- Slender Cones;
- Temperature Gradients;
- Heat Transfer Coefficients;
- Stagnation Temperature;
- Wind Tunnel Tests;
- Fluid Mechanics and Heat Transfer