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A simple method for increasing the lift of airplane wings by means of flaps (1933)
NASA Technical Reports Server (NTRS) · leaf 10
Figs. 4c,5,6 K.A.C.A, Technical Memorandum Ho. 714 Figure 4c. - Lift coef- ficients of T/ing with flaps vs angle, of attack a s= 0.2t … + s/t =.28 Cutaway wing. Figaro 5,- Pressure distri- X s/t =.10 Flap deflected downward ■bution alaout A = Smooth wing smooth V7ing (hatched) and about wing with flap accord- Figure 6.- Lift values obtained from ing to figure 1(circle). preasure-distribution meas- urement vs ejqperimental angle of…NASA Technical Reports Server (NTRS)
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