Hydrogen Film Cooling With Incident and Swept-Shock Interactions in a Mach 6.4 Nitrogen Fre.pdf

Hydrogen Film Cooling With Incident and Swept-Shock Interactions in a Mach 6.4 Nitrogen Fre.pdf

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Hydrogen Film Cooling With Incident and Swept-Shock Interactions in a Mach 6.4 Nitrogen Fre

NASA Technical Memorandum 4603 Hydrogen Film Cooling With Incident and Swept-Shock Interactions in a Mach 6.4 Nitrogen Free Stream George C. Olsen and Robert J. Nowak Langley Research Center ? Hampton, Virginia June 1995 Printed copies available from the following: NASA Center for AeroSpace Information National Technical Information Service (NTIS) 800 Elkridge Landing Road 5285 Port Royal Road Linthicum Heights, MD 21090-2934 Springfield, VA 22161-2171 (301) 621-0390 (703) 487-4650 Available electronically at the following URL address: /ltrs/ltrs.html Introduction Film cooling has been proposed as a means of ther- mal protection to reduce the scramjet combustor wall heating loads and the fuel mass required for regenerative cooling alone. In this concept, some of the regeneratively heated hydrogen fuel is injected at a supersonic velocity parallel to the wall through small slots to provide a buffer layer between the hot engine core flow and the structure. In addition to thermal protection, film cooling may improve engine performance by reducing skin friction and providing thrust in the high Mach number operating range. A coordinated government and industry study was conducted (refs. 1 and 2) to define film cooling technol- ogy for application to scramjet engines and to identify areas that require further data. The experimental effort reported herein is an outgrowth of this study. Some aerothermal problems associated with hyper- sonic flows are summarized in reference 3. These prob- lems include determining heat fluxes in the regions of incident-shock (two-dimensional) and swept-shock (three-dimensional) interactions with turbulent boundary layers. An oblique shock incident on a turbulent bound- ary layer forms a two-dimensional flow field with a sepa- rate flow region, a “lambda” shock structure (the incident and separation shock combination), and a reattachment (reflected) shock (fig. 1(a)). The interaction region becomes steady state and the extent of the separati

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