Approximate analysis for effect of arbitrarily-distributed blowing on laminar boundary layer flow and pressure distribution around two-dimensional or axially-symmetric hypersonic blunt bodies; analysis is based on simplified integral method solution coupled with Newtonian model of inviscid flow around effective body shape defined by dividing streamline between blown and free stream gas; significant increases in local pressure are found when blowing is continued around nose into afterbody region. (32622)
Effect of gaseous injection on aerodynamics of transpiration-cooled hypervelocity bodies
ASME -- Aviation and Space -- Progress and Prospects
ASME -- Annual Aviation and Space Conference ; 1968 ; United States , Beverly Hills, CA Hypersonic flow
1968
8 pages
Aufsatz (Konferenz)
Englisch
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