HOWARD UNIV WASHINGTON DC WASHINGTON United States
This study extends the work of Smith to Mach numbers indicative of the hypersonic flight regime and correlate the results to the occurrence of transition. The existing model uses PSE to capture the fully nonlinear interaction of modes in a low-speed, non-reacting, compressible boundary layer. It has the capability to calculate the contributions to surface heating and skin friction from the interaction of homogeneous e.g. first-modesecond-mode and inhomogeneous mode interaction e.g. second-modecrossflow. This approach captures the more realistic conditions that occur in-flight.