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Full-scale investigation of an equilateral triangular wing having 10-percent-thick biconvex airfoil sections

Description: Report discussing an investigation of the low-speed characteristics of a wing with a triangular plan form, 60 degrees of sweepback at the leading edge, and 10-percent-thick biconvex airfoil sections. The purpose of the investigation was to determine the effects of semispan and full-span leading-edge and trailing-edge flaps on the longitudinal aerodynamic characteristics of the wing and the effects of a vertical fin on the lateral stability characteristics.
Date: September 30, 1948
Creator: Whittle, Edward F., Jr. & Lovell, J. Calvin
Partner: UNT Libraries Government Documents Department

Pressure Distribution Over an NACA 23012 Airfoil With an NACA 23012 External-Airfoil Flap

Description: Report presents the results of pressure-distribution tests of an NACA 23012 airfoil with an NACA 23012 external airfoil flap made in the 7 by 10-foot wind tunnel. The pressures were measured on the upper and lower surfaces at one chord section on both the main airfoil and on the flap for several different flap deflections and at several angles of attack. A test installation was used in which the airfoil was mounted horizontally in the wind tunnel between vertical end planes so that two-dimensional flow was approximated.
Date: 1938
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Observations of the Effect of Wing Appendages and Flaps on the Spread of Separation of Flow Over the Wing

Description: "The spread of the separation of flow on three tapered wings insymmetrical and unsymmetrical flow was observed with silk tufts. By equal thickness and chord distribution the wings manifested a different form of lifting line. The principal result of the study was that the wings alone first disclosed complete breakdown of the flow at the tips, even the one with twist, but that after adding fuselage and engine nacelles, the twisted wing broke down completely first in the wing center" (p. 1).
Date: September 1941
Creator: Hartwig, G.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Tests of Wing Flaps Suitable for Direct Control of Glide-Path Angle

Description: "Preliminary tests have been made for the purpose of obtaining a flap arrangement suitable for direct and immediate control of the steepness of the glide path of an airplane, a use for which present flaps are not satisfactory. An attempt has been made to develop a flap giving a reasonably high maximum lift coefficient with relatively low deflection and maintaining this value of the maximum lift coefficient with a large increase of deflection, the increase in deflection being accompanied by a large increase in drag. An arrangement was found that gave a maximum lift coefficient of approximately 1.90 for all flap deflections between 25 and 80 degrees, within which range the drag of the wing increased regularly to a large value" (p. 1).
Date: January 1936
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department

Investigation at Low Speed of 45 Degrees and 60 Degrees Sweptback, Tapered, Low-Drag Wings Equipped With Various Types of Full-Span, Trailing-Edge Flaps

Description: Note presenting an investigation to determine the low-speed aerodynamic characteristics of two sweptback, low-drag, tapered wings equipped with full-span split and slotted flaps and three special types of trailing-edge flaps. Two sweep angles of 45 and 60 degrees, measured at the quarter chord, were used. The effect of the flaps on drag and pitching moment is the same as that indicated by other test data available.
Date: October 1951
Creator: Harper, John J.
Partner: UNT Libraries Government Documents Department