Working charts for the determination of the lift distribution between biplane wings (1934)
NASA Technical Reports Server (NTRS) · leaf 9
irfoil. Afrfon. Maximnm mean camber, per cent of chord 10.62 2.0 Maximum mean camber, par cent of chord. 9.9 Maximum thickness, per cant of chord 6.4 Maximnm thickness, per cent of chord L0 .986 Gap/chord ratio Gap/chord ratio - L0 1.00 Chord ratio— Chord ratio 17^20" 0 Decalage, degree Stagger 0"… … Figure 16.—Influence of fuselage shape on lift of low-wing monoplane R.A. F. 16 Airfoil. . (modified) 2.0 Maximum mean camber, per cent of chord. 0.4 Maximnm thickness, per cent of chord .86 Gap/chord ratio 1.0 Chord ratio 0 Stagger, degree 2 Decalage, degrees Percentage overhang 6.8 24 Reference…
NASA Technical Reports Server (NTRS)
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