Computational analysis of laminar boundary layer separation on a slender cone at angle of attack

In this paper we compare the experimental results of a Mach 14.2 flow over a series of blunt cones at angle of attack with computational results of the same flow over the same cone. The experimental results come from a 1971 test by Stetson at the Aerospace Research Laboratories. The computational analysis was done with the Data Parallel Line Relaxation method. Surface pressure results on the leeward side of the cone, Pitot pressure surveys and surface streamlines all agreed with the experimental results. The computations under-predict the surface pressures on the wind side and in regions of strong cross flow for all cases. The source of this difference is unknown; several potential explanations are offered.