Author: Willis H. BraunPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description
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.
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: 
Author: United States. Wright Air Development Division
Author: 
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Aeronautics and Space Administration
Author: United States. National Aeronautics and Space Administration