The Effect of Multi-mode Induced Transition in a Hypersonic Boundary Layers
Technical Report,30 Sep 2015,29 Sep 2018
HOWARD UNIV WASHINGTON DC WASHINGTON United States
Pagination or Media Count:
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.
- Fluid Mechanics
- Military Aircraft Operations