Span load distribution for tapered wings with partial-span flaps (1937)
NASA Technical Reports Server (NTRS) · leaf 3
s 6 and 7. Standard section characteristics for the plain section and the section with a flap are sometimes tabulated in- stead of being plotted as in figure 2. In such a case the value of Ac, may be found from the formula Ac,=c,/^l-22j+a0(««b-a'o/) where is the slope of the section lift curve per… … Flap span, bf/by, lengths indicated a satisfactory agreement. The first Fiqdbe 3.—Values of lift Increments and Hf t-curre slopes for wings with partial-span conclusion given in reference 5 is: "A satisfactory de- flaps. teiruination, for all conditions of test, of the span load the effect of…
NASA Technical Reports Server (NTRS)
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