Laminar and Turbulent Boundary Layers on Slightly-Blunted Cones at Hypersonic Speeds

摘要

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. (Author)