Title: Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans
Abstract: Report presenting an investigation in the 19-foot pressure tunnel of two-tapered wings with NACA 230-series airfoil sections, straight leading edges, and constant-chord center sections. Lift, drag, and pitching-moment coefficients were determined for the plain wing and for each flap arrangement for a range of Reynolds numbers. The results indicated that the wing with the square center section has greater maximum lift coefficients and increments of maximum lift due to flap deflections than the wing with the rectangular center section.
Publication Year: 1943
Publication Date: 1943-10-01
Language: en
Type: article
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