Experimental Study of a Laminar Boundary Layer on a Body of Revolution.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The effects of angle of attack variation on the streamwise velocity profiles, the pressure distribution, and the separation point for a laminar boundary layer on the leeside centerline of an elliptical body of revolution were studied. On the leeside centerline for angles of attack greater than 12 deg the boundary layer velocity profiles behave in a dissimilar way to those of two dimensional flow and the pressure gradient deviates from the inviscid solution becoming favorable along the aft portion of the body. The separation initially moves forward on the centerline then moves aft for angles of attack greater than 3 deg. Author
- Fluid Mechanics