Hypersonic Boundary Layer Stability Analysis Using PSE-Chem

In this paper we introduce the boundary layer stability equation solver PSE-Chem. This software employs a physical model approach to studying supersonic and hypersonic boundary layers and it incorporates the relevant physics including thermal and chemical nonequilibrium eects. Reentry F, a Mach 20 5 cone with very small nose bluntness, is used as a test case to determine the N factor at transition. Our results are compared with published results from other researchers. Results are also presented which show, using the e N method, the stabilizing eect of increasing nose radius under these conditions. The sensitivity of the methods is illustrated in the ability to calculate how small nose radius changes aect the transition location at stations hundreds of nose radii downstream.