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Determination of the theoretical pressure distribution for twenty airfoils (1934)
NASA Technical Reports Server (NTRS) · leaf 5
"O (a- 6'46') (a = 2-4f) (a--l°2r) (a = -5-231) 1 Percent chord Percent chord Percent chord /do 20 40 60 80 16 L 20 40 60 80 L 20 40 60 80 Fiocee 7.—Theoretical pressnre distribution for the GBttlngen 387 airfoil. Lower surface Upper surface Ci = 1.50 Ci ' LOO Cl = 0.50 &'0 (a- T46') (a' 3o40-)… … 20 40 60 80 A0L 20 40 60 80 160 Figure 10.—Theoretical pressure distribution for the O 72 alrfolLNASA Technical Reports Server (NTRS)
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