Pressure measurements were obtained at Mach numbers from 0.80 to 1. 05; results indicate that highly swept shock originates at wing leading edge body juncture and has large influence on loading over inboard wing sections.
Investigation at transonic speeds of loading over 45° swept-back wing having aspect ratio of 3, taper ratio of 0.2, and NACA 65a004 airfoil sections
NASA -- Tech Note
1961
93 pages
Report
English
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