Compressible laminar boundary layer on a cone at high angle of attack
An approximate integral method is applied to the three-dimensional laminar boundarylayer equations, including the energy equation for Prandtl number equal to unity, to obtain a solution to the attached boundary layer on slender cones in hypersonic flight at high angles of attack. The velocity and total enthalpy profiles are of the Timman type. The crossflow velocity profile is a two-parameter family allowing for nonzero crossflow at streamline inflection points. Because of the high angles of attack considered, the solution includes the effect of large crossflow velocity on the boundary layer. Using the pressure data available in the literature, results for the heat transfer coefficient, surface shear stress direction, and position of separation are computed. The computations compare favorably with data from the literature.