Abstract
Two methods for determining wall friction in strongly perturbed supersonic turbulent boundary layers were compared. The two methods were found to agree well when the velocity profile displayed a region of logarithmic variation in the transformed plane. The best agreement was found in comparisons of the wall friction rather than the skin friction coefficient which requires determining boundary layer edge conditions, a difficult task in perturbed boundary layers.
| Original language | English (US) |
|---|---|
| State | Published - 1989 |
| Event | AIAA 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1989 - Buffalo, United States Duration: Jun 12 1989 → Jun 14 1989 |
Other
| Other | AIAA 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1989 |
|---|---|
| Country/Territory | United States |
| City | Buffalo |
| Period | 6/12/89 → 6/14/89 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Condensed Matter Physics
- Electrical and Electronic Engineering
- Engineering (miscellaneous)
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