Initial supersonic combustion facility measurementsA combustion test tunnel designed for continuous operation to 2000 K was assembled. Flow quality of a Mach 2 nozzle for use with this tunnel was examined using an array of impact probes. The performance of gas shields used to protect optical windows was examined using both shadowgraphs and planar laser induced iodine fluorescence. High speed videography was used to aid in design of pressure relief panels related to hydrogen combustion testing safety.
Document ID
19890059478
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Krauss, Roland H. (Virginia Univ. Charlottesville, VA, United States)
Whitehurst, R. Bradford, III (Virginia Univ. Charlottesville, VA, United States)
Abitt, John D., III (Virginia Univ. Charlottesville, VA, United States)
Segal, Corin (Virginia Univ. Charlottesville, VA, United States)
Mcdaniel, James C. (Virginia, University Charlottesville, United States)