NASA NTRS · 19980232074
Turbulent Boundary Layer on a Yawed Cone in a Supersonic Stream
Abstract
The momentum integral equations are derived for the boundary layer on an arbitrary curved surface, using a streamline coordinate system. Computations of the turbulent boundary layer on a slightly yawed cone are made for a Prandtl number of 0.729, wall to free-stream temperature ratios of 1/2, 1, and 2, and Mach numbers from 1 to 4. Deflection of the fluid in the boundary layer from outer stream direction, local friction coefficient, displacement surface, lift coefficient, and pitching-moment coefficient are presented.
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Braun, Willis H.. 1959-01-01. Turbulent Boundary Layer on a Yawed Cone in a Supersonic Stream. https://ntrs.nasa.gov/citations/19980232074
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