The boundary-layer transition on the Hypersonic International Flight Research Experimentation 5 flight vehicle was studied using a two-dimensional parabolized stability equation analysis. Four trajectory points were selected to cover the range of the flight in which the transition is expected to occur on the vehicle. To solve the parabolized stability equation, a mean flow solution was generated using a finite-volume Navier-Stokes solver. The stability analysis was then conducted on the leading-edge and centerline symmetry planes of the vehicle. It was found that the leading-edge planes are expected to follow second-mode instability growth. The centerline cases experienced a much more complicated growth that was mainly driven by a second mode but also showed higher growth modes. In particular, for the lowest-altitude case, the higher modes seemingly contributed to the maximum N-factor growth. This was caused by the complex boundary-layer profile that was induced by a pair of vortices along the centerline of the vehicle.
Bibliographical noteFunding Information:
This work was supported by the Air Force Office of Scientific Research under LRIR 10RB02COR. We would like to acknowledge Chris Alba and Joel Gronvall in helping with the STABL calculations.