A quiet tunnel investigation of hypersonic boundary-layer stability over a cooled, flared cone

摘要: A flared-cone model under adiabatic and cooled-wall conditions was placed in a calibrated, low-disturbance Mach 6 flow the stability of boundary layer investigated using prototype constant-voltage anemometer. The results were compared with linear-stability theory predictions good agreement found prediction second-mode frequencies growth. In addition, same 'N = 10' criterion used to predict boundary-layer transition subsonic, transonic, supersonic flows low freestream noise be applicable for hypersonic regime as well. Under conditions, unique set spectral data acquired that documents linear, nonlinear, breakdown regions associated low-noise conditions.