Shock Detachment from the Leading Edge of Delta Wings.
Final scientific rept.,
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO
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Angles of attack for shock wave detachment from the sharp leading edge of five delta wing models with flat compression surfaces were determined experimentally and the results are compared with analytical prediction methods. The wind tunnel experiments were performed at a free stream Mach number of 14.2 and a free stream Reynolds number per foot of 62,000. The angle of attack for shock wave detachment was experimentally determined by observing the flow of oil from the compression side of the model around the leading edge. Author
- Fluid Mechanics