Wind-tunnel research comparing lateral control devices, particularly at high angles of attack IV : floating tip ailerons on rectangular wings (1933)
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ations and both with and without the triangular end plates. The results are given in Figures 2 and 3. With the symmetrical tip ailerons (fig. 2) the maximum value of the ratio ftmai/C^Dmin occurs in nearly all six tests at a flap setting of about 2° up. Above this angle of attack as the flap angle… … 0° 20° 4° 8° 12° 16° Flap angle, trailing edge up Tests with aileronflaps deflected.—Preliminary tests with the idea of improving the lift and drag character- Figube 3.—Variation of maximum lift and the ratio of maTtmirm lift to minimum drag with flap angle. Clark V airfoil with Olark Y tip…
NASA Technical Reports Server (NTRS)
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