AC Plasma Anemometer for Hypersonic Mach Number Experiments

Description:

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:
Category(s):
Devices
For Information, Contact:
Arnaud Cottet
Licensing Professional
University of Notre Dame
(574) 631-9766
acottet@nd.edu
Inventors:
Thomas Corke
Eric Matlis
Sivaram Gogineni
Keywords:
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