Application of spikes ahead of blunt noses of bodies of revolution as means of drag reduction; results of heat transfer and pressure tests, obtained in Langley hypersonic wind tunnel are presented together with study of effect of transition position; where possible, separation phenomena is compared with available theory; Schlieren photographs.
Investigation of flow over spiked-nose hemisphere-cylinder at mach number of 6.8
NASA -- Tech Note
1959
59 pages
Report
English
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Flow field about hemisphere-cylinder body at Mach number of 7.3
Engineering Index Backfile | 1962
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