Pressure Distribution Over a Thick, Tapered and Twisted Monoplane Wing Model-NACA 81-J (1932)
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EE FOR AERONAUTICS Figures 9 to 15. Isometric total normal pressure The results are presented without corrections for diagrams, including C, P. loci. tunnel wall and blocldng effects which have not been Figure 16. Angles of zero C^f for each test section. evaluated up to the present for set-ups of… … Figure 3.—Manometer installation Figure 18. Total lateral center of pressure coeffi- earher wings given in Reference 1. When interpreting cient versus angle of attack, Cpy versus a. the results in terms of the full scale airplane, considera- Figure 19. Total bending moment coefficient versus tion…
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