Working charts for the determination of the lift distribution between biplane wings (1934)
NASA Technical Reports Server (NTRS) · leaf 3
d on the consideration that the effect of stagger) which can be used to obtain factors for gap/ overhang is due chiefly to a change in aspect ratio of chord ratios larger than 1 by straight-line interpola- one of the wings. If one wing has a smaller chord and tion. This relation is expressed by… … & Propeller 4, 0° stogger 8, - 30' - 3. RA.F. IS O' 10, - 30- D 30° — • Points determined by present rules, ref. I ■7o ■76 .6 .8 /.<? 1.4 1.0 .6 .8 AO l.a 1.4 Oattin- Olark TJ.S.J Propel- Q0ttin.R.A.F. AlrfoIL. Y 27 ler* gen 387 gen 133 16 Maximum mean camber, per cent chord 6.9 5.4 5.7 i.6 3.8 2.6…
NASA Technical Reports Server (NTRS)
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