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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

Low-Speed Investigation of a 0.16-Scale Model of the X-3 Airplane: Longitudinal Characteristics

Description: Report presenting a wind-tunnel investigation of the low-speed static longitudinal characteristics of a model of the X-3 airplane with the wing flaps neutral and deflected. Results regarding those characteristics with the flaps neutral, with the flaps fully deflected, in the presence of a ground plane, with the flaps partially deflected, and effect of miscellaneous changes of the model are provided.
Date: September 8, 1950
Creator: Delany, Noel K. & Hayter, Nora-Lee F.
Partner: UNT Libraries Government Documents Department

Two-Dimensional Wind-Tunnel Investigation of the NACA 64(Sub 1)-012 Airfoil Equipped With Two Types of Leading-Edge Flap

Description: Note presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the characteristics of leading-edge flaps used as high-lift devices. Data are given to show the section lift characteristics for a range of flap deflections and the pitching-moment characteristics and lift characteristics with leading-edge roughness for the optimum flap arrangements.
Date: May 1947
Creator: Fullmer, Felicien F., Jr.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Split Trailing-Edge Lift and Trim Flaps on a Tapered Wing With 23 Degree Sweepback

Description: Note presenting the results of force tests and pressure-distribution measurements from a wind-tunnel investigation to determine the effects of size and hinge location of lift and trim flaps on the lift and pitching moment characteristics of a semispan tapered wing with 23 degrees sweepback of the quarter-chord line. The flaps were tested with different chords, spans, and trim flaps. The results indicated that the static longitudinal stability of the sweptback wing, as indicated by the slope of the curves of pitching-moment coefficient against lift coefficient, was increased when the lift flaps were deflected, especially for the larger flaps.
Date: July 1947
Creator: Letko, William & Feigenbaum, David
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Aerodynamic Balancing of Upper-Surface Ailerons and Split Flaps

Description: This report presents the results of wind tunnel tests to determine the effectiveness of various methods of reducing the high control forces of unbalanced upper-surface ailerons and of unbalanced split flaps. A balanced split flap was developed that required control forces about half those of the unbalanced split flap when the balanced split flap was deflected to give approximately the same maximum lift.
Date: August 20, 1935
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Ordinary and Split Flaps on Airfoils of Different Profile

Description: Report presents the results of wind tunnel tests of the Clark Y, the NACA 23012 and the NACA 23021 airfoils equipped with full-span ordinary flaps and with full-span simple split flaps. The principal object of the tests was to determine the characteristics of the airfoils with ordinary flaps and in addition, to determine the relative merits of the various airfoils when equipped with either ordinary flaps or with simple split flaps. The Clark Y airfoil was tested with 3 widths of ordinary flap, 10, 20, and 30 percent of the airfoil chord.
Date: October 25, 1935
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Effect of Power and Flaps on the Static Lateral Characteristics of a Single-Engine Low-Wing Airplane Model

Description: Tests were made in the Langley 7- by 10-foot tunnel to determine the lateral-stability characteristics with and without power of a model of a typical low-wing single-engine airplane with flaps neutral, with a full-span single slotted flap, and with a full-span double slotted flap. Power decreased the dihedral effect regardless of flap condition, and the double-slotted flap configuration showed the most marked decrease. The usual effect of power in increasing the directional stability was also shown.
Date: June 1947
Creator: Tamburello, Vito & Weil, Joseph
Partner: UNT Libraries Government Documents Department

Low-Speed Investigation of the Stalling of a Thin, Faired, Double-Wedge Airfoil with Nose Flap

Description: Note presenting an investigation of the stalling characteristics of a 4.23-percent-thick, faired, double-wedge airfoil section with and without a plain nose flap. Flap chord equal to 12, 16, 20, and 25 percent of the airfoil chord were tested.
Date: August 1950
Creator: Rose, Leonard M. & Altman, John M.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Boundary Layer and Wake and Their Relation to Airfoil Characteristics - NACA 65(Sub 1)-012 Airfoil With a True Contour Flap and a Beveled-Trailing-Edge Flap

Description: Note presenting two-dimensional flow tests conduced in the 2.5-by 6-foot test section of the stability tunnel on an NACA 65(sub 1)-012 airfoil with a true contour flap and a beveled-trailing-edge flap to determine lift, drag, hinge moment, boundary layer, and wake characteristics. Measurements indicated that the static-pressure gradient through a boundary layer may be large in regions where the airfoil has a small radius of curvature and that a static-pressure rise exists at the vertical position of minimum wake velocity for a region just behind the trailing edge.
Date: June 1947
Creator: Mendelsohn, Robert A.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Having a 30-Percent-Chord Trailing-Edge Flap at a Mach Number of 6.9

Description: Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.
Date: June 5, 1956
Creator: Ridyard, Herbert W. & Fetterman, David E., Jr.
Partner: UNT Libraries Government Documents Department

Theoretical Analyses to Determine Unbalanced Trailing-Edge Controls Having Minimum Hinge Moments Due to Deflection at Supersonic Speeds

Description: Memorandum presenting analyses based on theoretical results of NACA Report 1041 to determine the plan forms of unbalanced trailing-edge flap-type controls with minimum hinge moments due to deflection and requiring minimum work to overcome the hinge moments due to deflection at supersonic speeds. Results of the analyses for longitudinal controls show high-aspect-ratio untapered controls to possess maximum ratios of lift to hinge moment. Results regarding ratios of lift to hinge moment, ratios of lift to deflection work, ratios of rolling moment to hinge moment, and ratios of rolling moment to deflection work are provided.
Date: November 19, 1952
Creator: Goin, Kennith L.
Partner: UNT Libraries Government Documents Department

Characteristics of a 15-Percent-Chord and a 35-Percent-Chord Plain Flap on the NACA 0006 Airfoil Section at High Subsonic Speeds

Description: Memorandum presenting wind-tunnel tests to determine the aerodynamic characteristics of a 15-percent- and a 35-percent-chord plain trailing-edge flap on the NACA 0006 airfoil section. Simultaneous measurements of section lift, drag, and pitching moment were made over a range of Mach numbers, angles of attack, and flap deflections.
Date: October 2, 1947
Creator: Ilk, Richard J.
Partner: UNT Libraries Government Documents Department

Calculated Effect of Various Types of Flap on Take-Off Over Obstacles

Description: "In order to determine whether or not flaps could be expected to have any beneficial effect on take-off performance, the distances required to take off and climb to an altitude of 50 feet were calculated for hypothetical airplanes, corresponding to relatively high-speed types and equipped with several types of flap. The types considered are the Fowler wing, the Hall wing, the split flap, the balanced split flap, the plain flap, and the external-airfoil flap. The results indicate that substantial reductions in take-off distance are possible through the use of flaps, provided that the proper flap angle corresponding to a given set of conditions is used" (p. 1).
Date: May 1936
Creator: Wetmore, J. W.
Partner: UNT Libraries Government Documents Department

The Calculated Effect of Trailing-Edge Flaps on the Take-Off of Flying Boats

Description: "The results of take-off calculations are given for an application of simple trailing-edge flaps to two hypothetical flying boats, one having medium wing and power loading and consequently considerable excess of thrust over total resistance during the take-off run, the other having high wing and power loading and a very low excess thrust. For these seaplanes the effect of downward flap settings was: (1) to increase the total resistance below the stalling speed, (2) to decrease the get-away speed, (3) to improve the take-off performance of the seaplane having considerable excess thrust, and (4) to hinder the take-off of the seaplane having low excess thrust" (p. 1).
Date: November 1934
Creator: Parkinson, J. B. & Bell, J. W.
Partner: UNT Libraries Government Documents Department

The Development of a Lateral-Control System for Use With Large-Span Flaps

Description: "A spoiler-type lateral-control system has been developed for use on the Northrop P-61 airplane. The lateral-control system is to be used with large-span flaps and consists of a thin circular arc spoiler, linked with a short-span plain aileron located just outboard of the spoiler. This unconventional lateral-control system has been accepted with enthusiasm by the pilots who have flown the airplane" (p. 1).
Date: January 1946
Creator: Ashkenas, I. L.
Partner: UNT Libraries Government Documents Department

The effectiveness at high subsonic Mach numbers of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section

Description: Report presenting an analysis of the effectiveness of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section from section lift-coefficient data obtained at Mach numbers from 0.30 to 0.875. Results regarding effectiveness of the plain flap as a lift-producing device, and a comparison of the effectiveness of a spoiler, a dive-recovery flap, and a plain flap are provided.
Date: March 1954
Creator: Stivers, Louis S., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

Description: Report presenting the results of an investigation of flap-type controls on a low-aspect-ratio triangular wing using NACA 0005-63 sections for a constant-chord and a constant-percent-chord control surface. Two flap profiles were investigated: one with a true contour and the other with a blunt trailing edge. Results regarding lift, drag, pitching moment, hinge moment, and rolling moments were obtained for several Mach numbers, a constant Reynolds number, and a range of angles of attack.
Date: July 22, 1952
Creator: Boyd, John W.
Partner: UNT Libraries Government Documents Department

Some effects of propeller operation and location on ability of a wing with plain flaps to deflect propeller slipstreams downward for vertical take-off

Description: Report presenting an investigation to determine the effects of several factors associated with the propeller installation on the ability of a wing with plain flaps to deflect a propeller slipstream downward as a means for achieving vertical take-off. Some of the factors considered were propeller blade angle, mode of propeller rotation, propeller location, and ratio of wing chord to propeller diameter.
Date: January 1955
Creator: Draper, John W. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

An investigation at low speed of a 51.3 degree sweptback semispan wing equipped with 16.7-percent-chord plain flaps and ailerons having various spans and three trailing-edge angles

Description: Report presenting a wind-tunnel investigation performed at low speed to determine the aerodynamic characteristics of a 51.3 degree sweptback semispan wing equipped with 16.7-percent-chord plain flaps and ailerons with various spans and spanwise locations and one with span of aileron with trailing-edge angles of 6, 14, and 25 degrees. Results regarding the wing aerodynamic characteristics, aileron-control characteristics, spoiler control characteristics, and effect of wing-tip shape are provided.
Date: November 12, 1948
Creator: Fischel, Jack & Schneiter, Leslie E.
Partner: UNT Libraries Government Documents Department

Lateral-control investigation of flap-type controls on a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: transonic bump method

Description: Report presenting an investigation by the transonic-bump method through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls of various spans and locations. The wing of the semispan fuselage-wing combination had 60 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.
Date: March 2, 1950
Creator: Vogler, Raymond D.
Partner: UNT Libraries Government Documents Department

Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps

Description: Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils.
Date: April 1946
Creator: Pardee, Otway O'M. & Heaslet, Max A.
Partner: UNT Libraries Government Documents Department

Flight tests of a balanced split flap with particular reference to rapid operation

Description: The flight path of a small parasol monoplane equipped with a special type of balanced split flap was determined for a series of glides during which the time taken to deflect or retract the flap was varied from 1 to 15 seconds in order to study the effect of the time taken to complete a flap movement on the motion of an airplane between the start of a flap movement and the attainment of steady flight with the new flap setting. For flap movements accompanied by a change of lift characteristics, and consequently of velocity, there is an appreciable delay in obtaining a desired change in glide angle even though the flap is operated instantaneously. Immediate control of the glide path is obtained only when the speed is maintained during the flap movement. When the speed is changed, the deviation from the desired path during the transition increases in proportion to the rapidity with which the flap is moved so that, with a high-lift flap, abrupt retraction at speeds less than the minimum speed with the flap retracted may be dangerous if practiced close to the ground.
Date: December 1935
Creator: Soulé, H. A.
Partner: UNT Libraries Government Documents Department

Investigation of a thin wing of aspect ratio 4 in the Ames 12-foot pressure wind tunnel 4 : the effect of a constant-chord leading-edge flap at high subsonic speeds

Description: Report presenting wind-tunnel tests of a semispan model of a thin sharp-edged unswept wing of aspect ratio 4 and taper ratio 0.5 equipped with a full-span, constant-chord, leading-edge flap. The effectiveness of the leading-edge flap in improving the lift-drag ratio of the wing was investigated over a range of Mach and Reynolds numbers. Results regarding the lift characteristics, drag characteristics, pitching-moment characteristics, and lift-drag ratio are provided.
Date: January 20, 1949
Creator: Johnson, Ben H., Jr. & Reed, Verlin D.
Partner: UNT Libraries Government Documents Department

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel. 2: The Effect of Constant-Chord Leading- and Trailing-Edge Flaps on the Low-Speed Characteristics of the Wing

Description: Memorandum presenting wind-tunnel tests of a semispan model of an unswept wing of aspect ratio 4 and a taper ratio of 0.50, equipped with leading- and trailing-edge flaps. The purpose of the tests was to determine the low-speed aerodynamic characteristics of the wing as affected by the separate or combined deflections of a full-span, constant-chord, leading-edge, plain flap and a partial-plan, constant-chord, trailing-edge flap of either the plain or split type. Results regarding the maximum lift characteristics, pitching-moment characteristics, drag coefficients, lift-drag ratio, and effect of Reynolds number and profile modification are provided.
Date: October 18, 1948
Creator: Johnson, Ben H., Jr. & Bandettini, Angelo
Partner: UNT Libraries Government Documents Department