The effectiveness at high subsonic Mach numbers of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section
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The effectiveness at high subsonic Mach numbers of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section, report, March 1954; (https://digital.library.unt.edu/ark:/67531/metadc57107/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.