The drag of ridges of finite length in a turbulent boundary layer
Abstract
The drag due to ridges of rectangular and rounded sections and finite length were measured at Mach numbers of 0.73 and 2.52 using a skin-friction type balance mounted in the sidewall of a wind tunnel. Results are given for a single ridge and one mounted behind the other. The interference between two rectangular ridges is unfavorable at M = 0.73 but favorable at M = 2.52. For rounded ridges the drag is appreciably less, and little interference is apparent for both Mach numbers.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- July 1975
- Bibcode:
- 1975STIN...7610410K
- Keywords:
-
- Aerodynamic Drag;
- Surface Roughness;
- Turbulent Boundary Layer;
- Aerodynamic Coefficients;
- Mach Number;
- Skin Friction;
- Wind Tunnel Walls;
- Fluid Mechanics and Heat Transfer