LAMINAR AND TURBULENT BOUNDARY LAYERS ON SLIGHTLY-BLUNTED CONES AT HYPERSONIC SPEEDS
NAVAL ORDNANCE LAB WHITE OAK MD
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A momentum-integral method for calculating the boundary-layer growth on slightly-blunted cones has been given in a previous paper by the writer. The method, which was applied to cones with fully laminar flow, is extended in the present paper to turbulent flow. In addition 1 transition data on cones at hypersonic speeds are examined to show the great effect of slight nose blunting on interpretation of the results, 2 agreement between measured and calculated cone drag coefficients for fully laminar flow is demonstrated, and 3 turbulent friction and boundary-layer thickness calculations are shown to agree with the limited amount of ballistics range data which are available.
- Fluid Mechanics