AC Plasma Anemometer for Hypersonic Mach Number Experiments


Method and system for obtaining flow information, especially useful for high Mach number situations such as:

  • Understand mechanisms of stability and transition to turbulence caused by high speed boundary layer
  • Understand high-speed flows in compressors and turbines
  • Understand and monitor combustion instability in gas turbine engines
  • Design supersonic inlets for air breathing engines of supersonic aircraft
  • Understand and monitor 'unstart' in supersonic combustion (SCRAM) engines


Patent Information:
For Information, Contact:
Richard Cox
Director, Licensing & Business Development
University of Notre Dame
(574) 631-5158
Thomas Corke
Eric Matlis
Sivaram Gogineni
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