Experiments in Fluids

, Volume 33, Issue 2, pp 225–232

Supersonic boundary-layer response to optically generated freestream disturbances


  • J. D. Schmisseur
    • Air Force Office of Scientific Research AFOSR/NA 801 N Randolph St Rm 732 Arlington VA 22203-1977, USA e-mail: john.Schmisseur@afosr.af.mil
  • S. P. Schneider
    • Purdue University W. Lafayette, IN 47907, USA
  • S. H. Collicott
    • Purdue University W. Lafayette, IN 47907, USA

DOI: 10.1007/s00348-001-0392-5

Cite this article as:
Schmisseur, J., Schneider, S. & Collicott, S. Experiments in Fluids (2002) 33: 225. doi:10.1007/s00348-001-0392-5


Controlled, localized disturbances were introduced into the supersonic freestream upstream of a 4:1 elliptic cross-section cone. The response of the initially laminar boundary layer to the laser-generated freestream perturbation was measured above the cone minor axis. The experiment was conducted in the Mach-4 Purdue Quiet-flow Ludwieg tube at a freestream unit Reynolds number of 4.5 million/m. The focused beam from a frequency-doubled Nd:YAG laser was used to generate the disturbance. The perturbation existed in the flowfield as a region of locally heated air, referred to here as the thermal spot. Constant-temperature anemometry was used to characterize the boundary-layer response to the introduction of the thermal spot. The response was largest and most complex near the boundary-layer edge. The duration of the measured boundary-layer response was an order of magnitude greater than the measured duration of the disturbance in the freestream. Within the boundary layer, the mass-flux deviation introduced by the thermal spot was of the same magnitude as the local mean mass flux. The optically generated disturbance is potentially useful as a perturbation source in future boundary-layer receptivity experiments.

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© Springer-Verlag Berlin Heidelberg 2002