Parametric and time resolved studies of autoignition and flameholding in a clean-air supersonic combustorA model scramjet combustor was tested using transverse sonic injection of gaseous hydrogen behind a rearward facing step. It was found that ignition in the constant area duct initiates well downstream and propagates upstream with velocities ranging from 300 to nearly 1,000 m/s in the laboratory frame. The downstream ignition develops into a detonation wave prior to reaching the region of observation. A number of parameters including fuel flow rate, air stagnation temperature and pressure, and the operating conditions of the downstream air ejector affected ignition conditions.
Document ID
19920066359
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Whitehurst, R. B. (NASA Langley Research Center Hampton, VA, United States)
Krauss, R. H. (NASA Langley Research Center Hampton, VA, United States)
Mcdaniel, J. C. (Virginia, University Charlottesville, United States)