Working charts for the determination of the lift distribution between biplane wings (1934)
NASA Technical Reports Server (NTRS) · leaf 6
dynamic investigators narily be expected because a rather large opening have realized that it is important to test not only com- existed between the root of the wing and the fuselage. ponent parts of the airplane, but also the complete Tests on the influence of a fuselage on the wings of a… … fGJttingen Airfoil. 133 fGBttingen Airfoil I 133 Maximum mean camber, per cent chord. 4.6 8.1 Maximum thickness, per cent chord 4.6 Maximum mean camber, par cent chord. Gap/chord ratio _ .67 8.1 Mairimnm thickness, per cent chord Chord ratio — LO .67 Gap/chord ratio • 0 Stagger, degree 1.0 Chord…
NASA Technical Reports Server (NTRS)
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