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Calculation of tapered monoplane wings (1930)
NASA Technical Reports Server (NTRS) · leaf 22
N.A.C.A. Technical Memorandum Ho.578 Figs.4a,4b,4c,5,6a, 6b … a, cL= 1.0 d,cU-0.5 g,oU0.25 b, » = 0.5 e, ••=-1.0 h,»=-0.25 c, 0 f, »= 0.75 i,«=-0.75 Fig.4a,b,c Circulation distributions r according to eq.l along the half- r/rr span for dif - r ferent coef A "XJ ficients cL i x = b/2 |=x=0 Fig.5 Deduction of bending moment. 1.0 0.8 0.6 0.4 0 -0.1 .8 1.0 .2 .4…NASA Technical Reports Server (NTRS)
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