An Experimental Investigations of the Stability of the Laminar Boundary Layer on a Cone at M=8,
AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH
Pagination or Media Count:
The stability of the laminar boundary layer on a 7-degree half angle cone at M infinity 8 was experimentally investigated using hot-wire anemometry techniques. The principle instability of the hypersonic boundary layer was associated with second mode disturbances. The frequency of the most amplified disturbances was directly related to the boundary layer thickness. Small nosetip bluntness was found to make significant changes, compared to a sharp cone, in the stability characteristics of the boundary layer.