Wind-tunnel investigation of ordinary and split flaps on airfoils of different profile (1937)
NASA Technical Reports Server (NTRS) · leaf 11
have shown that actually the 7- by 10-foot wind tunnel and 2.6 for the variable- the increments in maximum lift due to split flaps on density wind tunnel. The data show that the scale medium-thick airfoils vary but little with Reynolds effect is about the same for the N. A. C. A. 23021 air- Number.… … --a,e 24 30 0 8 16 -8 Fiquke 28.—Lift-drag ratio and pltchlng-moment coefflolrat for tho cC, degrees N. A. C. A. 23021 airfoil with 0.20c full-span split flap. Figure 28.—Lift, drag, and center of pressure for the N.A.O.A. 23021 airfoil with <X20c f uH-epan spirt flap. the plain airfoil and that…
NASA Technical Reports Server (NTRS)
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