Crossflow instability in a hypersonic boundary layer Academic Article uri icon


  • The crossflow instability in a hypersonic, laminar boundary layer is investigated using point measurements inside the boundary layer for the first time. Experiments are performed on a 7 right, circular cone with an adiabatic wall condition at 5.6 angle of incidence in the low-disturbance Mach 6 Quiet Tunnel at Texas A&M University. Measurements are made with a constant-temperature hot-wire anemometer system with a frequency response up to 180kHz. Stationary crossflow waves are observed to grow and saturate. A travelling wave coexists with the stationary wave and occurs in a frequency band centred around 35kHz. A type-I secondary instability is also observed in a frequency band centred around 110kHz. The behaviour of all three modes is largely consistent with their low-speed counterparts prior to saturation of the stationary wave. Afterward, the behaviour remains in partial agreement with the low-speed case. Neither type-II secondary instability nor transition to turbulence are observed in this study.

published proceedings


author list (cited authors)

  • Craig, S. A., & Saric, W. S.

citation count

  • 73

complete list of authors

  • Craig, Stuart A||Saric, William S

publication date

  • December 2016