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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Technical Notes
 Collection: Technical Report Archive and Image Library
Wind-tunnel tests of the Fowler variable-area wing

Wind-tunnel tests of the Fowler variable-area wing

Date: May 1, 1932
Creator: Weick, Fred E
Description: The lift, drag, and center of pressure characteristics of a model of the Fowler variable-area wing were measured in the NACA 7 by 10 foot wind tunnel. The Fowler wing consists of a combination of a main wing and an extension surface, also of airfoil section. The extension surface can be entirely retracted within the lower rear portion of the main wing or it can be moved to the rear and downward. The tests were made with the nose of the extension airfoil in various positions near the trailing edge of the main wing and with the surface at various angular deflections. The highest lift coefficient obtained was C(sub L) = 3.17 as compared with 1.27 for the main wing alone.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of wing flaps suitable for direct control of glide-path angle

Wind-tunnel tests of wing flaps suitable for direct control of glide-path angle

Date: January 1, 1936
Creator: Weick, Fred E
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.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests on a model of a monoplane wing with floating ailerons

Wind tunnel tests on a model of a monoplane wing with floating ailerons

Date: September 1, 1929
Creator: Knight, Montgomery
Description: This report describes preliminary wind tunnel tests on a model of a monoplane wing equipped with wing tip floating ailerons. Lift and drag, as well as rolling and yawing moments, were measured.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests on airfoil boundary control using a backward opening slot

Wind tunnel tests on airfoil boundary control using a backward opening slot

Date: October 1, 1929
Creator: Knight, Montgomery
Description: This report presents the results of an investigation to determine the effect of boundary layer control on the lift and drag of an airfoil equipped with a backward opening slot. Various slot locations, widths of opening, and pressures, were used. The tests were conducted in the Five-Foot Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. The greatest increase in maximum lift was 96 per cent, the greatest decrease in minimum drag was 27 per cent, and the greatest increase in the ratio, maximum lift coefficient/minimum drag coefficient, was 151 per cent.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests on an airfoil equipped with a split flap and a slot

Wind tunnel tests on an airfoil equipped with a split flap and a slot

Date: October 1, 1929
Creator: Bamber, Millard J
Description: The investigation described in this report is concerned with the changes in the aerodynamic characteristics of an airfoil which are produced by a gauze-covered suction slot, located near the leading edge, and connected by an air passage to a split flap at the trailing edge. The tests were conducted at the Langley Memorial Aeronautical Laboratory. At the larger values of lift coefficient where the action of the slot might be expected to be most effective, the pressure differences were such that the air flowed out of the slot rather than in through it, and in consequence, the maximum lift coefficient was decreased.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests on model wing with Fowler flap and specially developed leading-edge slot

Wind-tunnel tests on model wing with Fowler flap and specially developed leading-edge slot

Date: May 1, 1933
Creator: Weick, Fred E
Description: An investigation was made in the NACA 7 by 10 foot wind tunnel to find the increase in maximum lift coefficient which could be obtained by providing a model wing with both a Fowler trailing-edge extension flap and a Handley Page type leading-edge slot. A conventional Handley page slot proportioned to operate on the plain wing without a flap gave but a slight increase with the flap; so a special form of slot was developed to work more effectively with the flap. With the best combined arrangement the maximum lift coefficient based on the original area was increased from 3.17, for the Fowler wing, to 3.62. The minimum drag coefficient with both devices retracted was increased in approximately the same proportion. Tests were also made with the special-type slot on the plain wing without the flap. The special slot, used either with or without the Fowler flap, gave definitely higher values of the maximum lift coefficient than the slots of conventional form, with an increase of the same order in the minimum drag coefficient.
Contributing Partner: UNT Libraries Government Documents Department
Wing-body combinations with certain geometric restraints having low zero-lift wave drag at low supersonic Mach numbers

Wing-body combinations with certain geometric restraints having low zero-lift wave drag at low supersonic Mach numbers

Date: February 1, 1956
Creator: Lomax, Harvard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing-body interference at supersonic speeds with an application to combinations with rectangular wings

Wing-body interference at supersonic speeds with an application to combinations with rectangular wings

Date: April 1, 1952
Creator: Nielsen, Jack N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing plan forms for high-speed flight

Wing plan forms for high-speed flight

Date: March 1, 1946
Creator: Jones, Robert T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing pressure-distribution measurements up to 0.866 Mach number in flight on a jet-propelled airplane

Wing pressure-distribution measurements up to 0.866 Mach number in flight on a jet-propelled airplane

Date: March 1, 1947
Creator: Brown, Harvey H
Description: None
Contributing Partner: UNT Libraries Government Documents Department