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Exploratory investigation of an airfoil with area suction applied to a porous, round trailing edge fitted with a lift-control vane

Description: Report presenting a two-dimensional wind-tunnel investigation of the effectiveness of area suction near the trailing edge for increasing the lift of an NACA 65(sub 1)-012 airfoil modified to incorporate a porous, round trailing edge. The modified section had a thickness-chord ratio of 0.16 and a thin, small chord vane on the round trailing edge. Results regarding the model with vane, model without vane, model with faired vane, control surface, and comparison with similar lift-control devices are provided.
Date: April 1955
Creator: Dannenberg, Robert E. & Weiberg, James A.
Partner: UNT Libraries Government Documents Department

Section characteristics of a 10.5-percent-thick airfoil with area suction as affected by chordwise distribution of permeability

Description: Report presenting an investigation at low speed of the two-dimensional aerodynamic characteristics of a 10.51-percent-thick symmetrical airfoil with area suction near the leading edge. The chordwise extent and distribution of porosity were adjusted in order to obtain a low quantity of suction-air flow for the maximum possible lift. Results regarding the plain wing, wing with various chordwise extents of area suction, wing with area suction from the leading edge to 3-percent chord, boundary-layer measurements, and stagnation location are provided.
Date: December 1952
Creator: Dannenberg, Robert E. & Weiberg, James A.
Partner: UNT Libraries Government Documents Department

Preliminary Wind-Tunnel Investigation of the Effect of Area Suction on the Laminar Boundary Layer Over an NACA 64A010 Airfoil

Description: Memorandum presenting a preliminary investigation made in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Although the airfoil surface had many waves and irregularities of contour, the data corroborated qualitatively the theoretically predicted stabilizing effect of area suction on a smooth flat plate.
Date: April 26, 1948
Creator: Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

Large-Scale Wind-Tunnel Tests of an Airplane Model With a 45 Degree Sweptback Wing of Aspect Ratio 2.8 With Area Suction Applied to Trailing-Edge Flaps and With Several Wing Leading-Edge Modifications

Description: Memorandum presenting an investigation of an airplane model to determine the effect of area suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. The wing had an aspect ratio of 2.8 and a taper ratio of 0.17.
Date: November 2, 1956
Creator: Koenig, David G. & Aoyagi, Kiyoshi
Partner: UNT Libraries Government Documents Department

Effect of Type of Porous Surface and Suction Velocity Distribution on the Characteristics of a 10.5 Percent-Thick Airfoil With Area Suction

Description: Note presenting an investigation at low speed of the two-dimensional characteristics of a 10.51-percent-thick symmetric airfoil with area suction for boundary-layer control near the leading edge. The lift and suction-flow characteristics were determined with different porous surfaces consisting of perforated plates and sintered steel for various suction velocity distributions obtained by varying the permeability arrangement.
Date: December 1953
Creator: Dannenberg, Robert E. & Weiberg, James A.
Partner: UNT Libraries Government Documents Department

Experimental Study of the Effects of Finite Surface Disturbances and Angle of Attack on the Laminar Boundary Layer of an NACA 64A010 Airfoil With Area Suction

Description: Note presenting a low-turbulence wind-tunnel investigation of an NACA 64A010 airfoil section with continuous suction through its porous surfaces to determine its ability to maintain extensive laminar flow behind finite surface disturbances and at angles of attack other than 0 degrees. Generally, application of area suction permitted only a small increase in the size of a finite disturbance required to cause premature boundary-layer transition as compared with the nonsuction airfoil.
Date: October 1952
Creator: Schwartzberg, Milton A. & Braslow, Albert L.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the use of leading-edge and trailing-edge area-suction flaps on a 13-percent-thick straight wing and fuselage model

Description: Report presenting a wind-tunnel investigation to determine the effectiveness of area suction in increasing the lift of a moderately thick straight wing encountering trailing-edge air flow separation. Results regarding a model with undeflected leading-edge flap and tip tanks on and a model with the tip tanks removed are provided.
Date: January 24, 1958
Creator: Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

Wind-tunnel and flight investigations of the use of leading-edge area suction for the purpose of increasing the maximum lift coefficient of a 35 degree swept-wing airplane

Description: From Summary: "An investigation was undertaken to determine the increase in maximum lift coefficient that could be obtained by applying area suction near the leading edge of a wing. This investigation was performed first with a 35 degree swept-wing model in the wind tunnel, and then with an operational 35 degree swept-wing airplane which was modified in accord with the wind-tunnel results. The wind-tunnel and flight tests indicated that the maximum lift coefficient was increased more than 50 percent by the use of area suction. Good agreement was obtained in the comparison of the wind-tunnel results with those measured in flight."
Date: 1956
Creator: Holzhauser, Curt A. & Bray, Richard S.
Partner: UNT Libraries Government Documents Department

The use of area suction to increase the effectiveness of a trailing-edge flap on a triangular wing of aspect ratio 2

Description: From Summary: "A wind-tunnel investigation was conducted to determine the effect of applying area-suction boundary-layer control to a constant-chord plain flap on a triangular wing of aspect ratio 2. The results showed that with small amounts of suction applied near the leading edge of the flap, high lift at relatively low attitudes can be obtained." The typical lift, drag, pitching-moment data, effects of the porous area, effects of suction, and comparison of theoretical and experimental flap lift are described.
Date: April 1, 1954
Creator: Kelly, Mark W. & Tolhurst, William H., Jr.
Partner: UNT Libraries Government Documents Department

The use of area suction for improving the longitudinal characteristics of a thin unswept wing-fuselage model with leading- and trailing-edge flaps

Description: From Summary: "An investigation was conducted to determine the effect of porous area suction applied to the knees of full-span leading-edge and part-span trailing-edge flaps installed on an unswept-wing airplane model." The results obtained from an angle of attack of 0 degrees and greater than 0 degrees are compared. The effect of deflection, suction requirements, and stability characteristics are described.
Date: July 10, 1956
Creator: Koenig, David G.
Partner: UNT Libraries Government Documents Department

The use of area suction for the purpose of improving trailing-edge flap effectiveness on a 35 degree sweptback wing

Description: From Summary: "An investigation was conducted to determine the effectiveness of suction applied through a porous area at the leading edge of the flap, on a 35 degree sweptback wing. Several chordwise extents and positions of area suction were tested for the suction flap deflected 55 degrees and 70 degrees. The results indicated that large increases in flap lift increment can be made by applying suction with very small flow quantities to an area near the leading edge of a flap."
Date: July 2, 1953
Creator: Cook, Woodrow L.; Holzhauser, Curt A. & Kelly, Mark W.
Partner: UNT Libraries Government Documents Department

The use of area suction for the purpose of delaying separation of air flow at the leading edge of a 63 degree swept-back wing: effects of controlling the chordwise distribution of suction air velocities

Description: Report discusses the results of an updated investigation into the effectiveness of area suction when used to prevent air-flow separation at the leading edge of a 63 degree swept-back wing. This new report investigates the results of tests with chordwise distribution of the suction-air velocities controlled to give lower total-flow quantity requirements. The primary focus is the delay effected in air-flow separation and improvements made on aerodynamic characteristics of a wing with area suction specifically designed for a lift coefficient of 0.77.
Date: January 14, 1952
Creator: Cook, Woodrow L. & Kelly, Mark W.
Partner: UNT Libraries Government Documents Department

The use of area suction for the purpose of delaying separation of air flow at the leading edge of a 63 degree swept-back wing

Description: From Summary: "An investigation was conducted to determine the effectiveness of area suction used to delay the separation of air flow at the leading edge of a 63 degree swept-back wing. Changes in lift, drag, and pitching-moment data were correlated with the occurrence of the separation of the air flow by means of pressure-distribution data. It was found that the spanwise and the chordwise extent of area suction required to control leading-edge separation were in general agreement with that predicted by theory, but the quantity of flow required was considerably higher than predicted by theory."
Date: November 22, 1950
Creator: Cook, Woodrow L.; Griffin, Roy N., Jr. & McCormack, Gerald M., Jr.
Partner: UNT Libraries Government Documents Department

Preliminary wind-tunnel investigation of the effect of area suction on the laminar boundary layer over an NACA 64A010 airfoil

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. The surface of the airfoil that was tested had a lot of waves and irregularities, but the theoretically predicted stabilizing effect of area suction on a smooth flat plate was still observed.
Date: April 26, 1948
Creator: Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

Perforated sheets as the porous material for a suction-flap application

Description: Two-dimensional tests were made of an NACA 0006 airfoil with area suction applied to a porous region on a 0.3-chord trailing-edge flap deflected 50 degrees. The lift with suction approached the value computed from thin-airfoil theory. The lift gains and suction quantity requirements were unaffected by the perforation patterns of the surface over a wide range of hole sizes and spacings.
Date: May 1957
Creator: Dannenberg, Robert E.; Weiberg, James A. & Gambucci, Bruno J.
Partner: UNT Libraries Government Documents Department

A Fibrous-Glass Compact as a Permeable Material for Boundary-Layer-Control Applications Using Area Suction

Description: "Measurements were made of the resistance of fibrous-glass compacts to normal air flow. The flow resistance was related to the thickness and density. As a porous material for boundary-layer-control applications using area suction, the fibrous-glass compact could be made to any desired thickness and permeability and sandwiched between perforated rigid surfaces" (p. 1).
Date: January 1955
Creator: Dannenberg, Robert E.; Weiberg, James A. & Gambucci, Bruno J.
Partner: UNT Libraries Government Documents Department

Exploratory investigation of the use of area suction to eliminate air-flow separation in diffusers having large expansion angles

Description: Tests were made at a mean inlet Mach number of 0.2 with area suction applied to conical diffusers with expansion angles of 30 degrees and 50 degrees and exit to inlet area ratios of 2. Air-flow separation was eliminated with suction mass flows of 3 and 4 percent of the inlet mass flows for the 30 degrees and 50 degrees diffusers, respectively.
Date: October 1956
Creator: Holzhauser, Curt A. & Hall, Leo P.
Partner: UNT Libraries Government Documents Department

Area-Suction Boundary-Layer Control as Applied to the Trailing-Edge Flaps of a 35 Degree Swept-Wing Airplane

Description: "A wind-tunnel investigation was made to determine the effects on the aerodynamic characteristics of a 35 degree swept-wing airplane of applying area-suction boundary-layer control to the trailing-edge flaps. Flight tests of a similar airplane were then conducted to determine the effect of boundary-layer control in the handling qualities and operation of the airplane, particularly during landing. The wind-tunnel and flight tests indicated that area suction applied to the trailing-edge flaps produced significant increases in flap lift increment" (p. 1).
Date: May 6, 1958
Creator: Cook, Woodrow L.; Anderson, Seth B. & Cooper, George E.
Partner: UNT Libraries Government Documents Department

Flight Investigation of the Low-Speed Characteristics of a 35 Degree Swept-Wing Airplane Equipped with an Area-Suction Ejector Flap and Various Wing Leading-Edge Devices

Description: Memorandum presenting tests conducted to determine the flight characteristics of an F-86F airplane equipped with an area-suction-type boundary-layer control installation on the trailing-edge flaps. Measurements were made of the lift, drag, and engine bleed-air requirements. Results regarding the aerodynamic characteristics as well as some miscellaneous characteristics are provided.
Date: September 26, 1957
Creator: Anderson, Seth B.; Faye, Alan E., Jr. & Innis, Robert C.
Partner: UNT Libraries Government Documents Department