Accession Number:



Premixed Supersonic Combustion (Rev)

Descriptive Note:

Technical Report,01 Aug 2013,14 Sep 2014

Corporate Author:

University of Virginia Charlottesville United States

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Hypersonic air-breathing engines rely on scramjet combustion processes, which involve high speed, compressible, and highly turbulent flows. The combustion environment and the turbulent flames at the heart of these engines are difficult to simulate and study in the laboratory under well controlled conditions. Typically, wind-tunnel testing is performed that more closely approximates engine testing rather than a careful investigation of the underlying physics that drives the combustion process. The experiments described in this report, along with companion data sets developed separately, aim to isolate the chemical kinetic effects from the fuel-air mixing process in a dual-mode scramjet combustion environment. A unique fuel injection approach is taken that produces a uniform fuel-air mixture at the entrance to the combustor. This approach relies on the precombustion shock train upstream of the dual-mode scramjet combustor. A stable ethylene flame anchored on a cavity flame holder with a uniformly mixed combustor inflow was achieved in these experiments, allowing numerous companion studies involving coherent anti-Stokes Raman scattering CARS, particle image velocimetry PIV, and planar laser induced fluorescence PLIF to be performed.

Subject Categories:

  • Combustion and Ignition
  • Jet and Gas Turbine Engines

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