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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

Low-Speed Characteristics of a Wing Having 63 Degrees Sweepback and Uniform Camber

Description: Memorandum presenting low-speed tests of a semispan tapered wing with the leading edge swept back 63 degrees and with the NACA 0010 section cambered for a lift coefficient of 1.0 perpendicular to the leading edge to determine the extent to which stability characteristics could be improved by cambering the wing.
Date: June 26, 1951
Creator: Rose, Leonard M.
Partner: UNT Libraries Government Documents Department

A Method for the Design of Sweptback Wings Warped to Produce Specified Flight Characteristics at Supersonic Speeds

Description: Memorandum presenting a method for designing a wing to be self-trimming at a given set of flight conditions. The spanwise distribution of load on the wing is made to be approximately elliptical, in an effort to maintain low wing drag. The procedure is illustrated using several examples.
Date: September 12, 1951
Creator: Tucker, Warren A.
Partner: UNT Libraries Government Documents Department

A Method for the Design of Sweptback Wings Warped to Produce Specified Flight Characteristics at Supersonic Speeds

Description: One of the problems connected with the sweptback wing is the difficulty of controlling the location of the center of pressure and hence the pitching moment. A method is presented for designing a wing to be self-trimming at a given set of flight conditions. Concurrently, the spanwise distribution of load on the wing is made to be approximately elliptical, in an effort to maintain low wing drag.
Date: May 11, 1951
Creator: Tucker, Warren A.
Partner: UNT Libraries Government Documents Department

Supersonic Wave Drag of Nonlifting Sweptback Tapered Wings With Mach Lines Behind the Line of Maximum Thickness

Description: Note presenting a theoretical investigation of the supersonic wave drag of nonlifting sweptback tapered wings with thin symmetrical double-wedge airfoil sections with maximum thickness at 50 percent chord. For wings of equal root bending stress and given sweepback, taper increases the wing wave-drag coefficient at Mach numbers.
Date: August 1948
Creator: Margolis, Kenneth
Partner: UNT Libraries Government Documents Department

Formulas for the Supersonic Loading, Lift, and Drag of Flat Swept-Back Wings With Leading Edges Behind the Mach Line

Description: "The method of superposition of linearized conical flows has been applied to the calculation of the aerodynamic properties, in supersonic flight, of thin flat, swept-back wings at an angle of attack. The wings are assumed to have rectilinear plan forms, with tips parallel to the stream, and to taper in the conventional sense. The investigation covers the moderately supersonic speed range where the Mach lines from the leading-edge apex lie ahead of the wing" (p. 1147).
Date: March 15, 1950
Creator: Cohen, Doris
Partner: UNT Libraries Government Documents Department

Theoretical Distribution of Load Over a Swept-Back Wing

Description: Report presenting a calculation of the load over an elliptical wing with 30 degrees sweepback by a method, based on vortex theory, which takes account of the chordwise distributions of lifting area. The theory indicates a 14-percent loss in total lift due to the introduction of sweepback, with the greatest loss taking place at the center of the span.
Date: October 1942
Creator: Cohen, Doris
Partner: UNT Libraries Government Documents Department

Low-speed wind-tunnel investigation of the longitudinal stability characteristics of a model equipped with a variable-sweep wing

Description: Report presenting an investigation to determine the longitudinal stability characteristics of a complete model equipped with a variable-sweep wing at four different angles of sweepback. The primary objective was to study various wing modifications and an external-flap arrangement designed to minimize the shift in neutral point accompanying the change in sweep angle.
Date: May 23, 1949
Creator: Donlan, Charles J. & Sleeman, William C., Jr.
Partner: UNT Libraries Government Documents Department

An experimental study at moderate and high subsonic speeds of the flow over wings with 30 degrees and 45 degrees of sweepback in conjunction with a fuselage

Description: Report presenting pressure distributions, wake measurements, and tuft patterns for wings with 30 and 45 degrees of sweepback in conjunction with a midwing fuselage at Mach numbers to 0.96. The wings have an NACA 65-210 section, a taper ratio of 2.6:1, and aspect ratios of 7.5 and 5.2. The study indicated that when the Mach number reached high subsonic values at low angles of attack, the locations of peak negative pressure coefficients on the upper surfaces of the sections near the wing-fuselage junctures shifted rearward.
Date: June 15, 1951
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department

Longitudinal stability characteristics at Mach numbers up to 0.92 of a wing-body-tail combination having a wing with 45 degrees of sweepback and a tail in various vertical positions

Description: Report presenting wind-tunnel tests at a range of Mach numbers to measure the static longitudinal stability characteristics of a semispan wing-fuselage-tail model having a wing with 45 degrees of sweepback. The wing had an aspect ratio of 5.5 and had NACA 64A010 sections normal to the quarter-chord line. The center of pressure of the wing-fuselage combination moved forward as the wing began to stall, and a tail in the higher positions produced additional stalling moments due to high effective downwash.
Date: January 28, 1955
Creator: Stephenson, Jack D.; Bandettini, Angelo & Selan, Ralph
Partner: UNT Libraries Government Documents Department

Summary of the Aerodynamic Characteristics and Flying Qualities Obtained from Flights of Rocket-Propelled Models of an Airplane Configuration Incorporating a Sweptback Inversely Tapered Wing at Transonic and Low-Supersonic Speeds

Description: From Summary: "Flight tests have been conducted on rocket-propelled models of an airplane configuration incorporating a sweptback wing with inverse taper to investigate the drag, stability, and control characteristics at transonic and supersonic speeds. The models were tested with a conventional tail arrangement in the Mach number range from 0.55 to 1.2. In addition to the various aerodynamic parameters obtained, the flying qualities were computed for a full-scale airplane with the center-of-gravity location at 18 percent of the mean aerodynamic chord. Also, included in this investigation are drag measurements made on relatively simple fixed-control models tested with both conventional and V-tail arrangements."
Date: September 7, 1950
Creator: Mitcham, Grady L. & Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

Effects of leading-edge radius on the longitudinal stability characteristics of two 60 degree sweptback wings at high Reynolds numbers

Description: Report presenting tests on two 60 degree sweptback wings of aspect ratios 2 and 3 to provide information on the influence of leading-edge radius on the static longitudinal stability characteristics of swept wings.
Date: March 19, 1956
Creator: Schneider, William C.
Partner: UNT Libraries Government Documents Department

Pressure-distribution measurements over a 45 degree sweptback wing at transonic speeds by the NACA wing-flow method

Description: Report presenting measurements of pressure made over the chord of a swept-wing model at four stations along the span by the NACA wing-flow method. The model was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. Results regarding the chordwise pressure distributions and spanwise distributions of section lift, drag, and pitching moment.
Date: June 25, 1951
Creator: Danforth, Edward C. B. & O'Bryan, Thomas C.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Description: From Introduction: "The investigation reported herein was initiated to define further the effects on the aerodynamic characteristics and load distribution of a thin, sweptback wing of a low-pressure blowing system and also to provide information on which to base a more thorough study of a complete airplane configuration."
Date: September 20, 1955
Creator: Whittle, Edward F., Jr. & McLemore, H. Clyde
Partner: UNT Libraries Government Documents Department

Low-speed pressure distributions over the drooped-nose flap of a 42 degrees sweptback wing with circular-arc airfoil sections at a Reynolds number of 5.3 x 10(exp 6)

Description: Report presenting an investigation of the pressure distributions over the drooped-nose flap of a 42 degree sweptback wing with circular-arc airfoil sections and half-span trailing-edge split flaps in the 19-foot pressure tunnel. The effects of the deflection and span of the drooped-nose flap and effects of split trailing-edge flaps on the pressures over the drooped-nose flap were determined.
Date: September 23, 1948
Creator: Spooner, Stanley H. & Woods, Robert L.
Partner: UNT Libraries Government Documents Department

Effect of ground interference on the aerodynamic characteristics of a 42 degrees sweptback wing

Description: From Summary: "The effects of ground interference on the aerodynamic characteristics of a 42 degrees sweptback wing have been determined at distances above the ground 0.68 and 0.92 of the mean aerodynamic chord (measured from the 0.25 mean aerodynamic chord). The wing was tested without flaps and with inboard trailing-edge split and outboard leading-edge flaps deflected. The wing had an aspect ratio of 4, a taper ratio of 0.625, and NACA 641-112 airfoil sections perpendicular to the 0.273 chord line. The results are, in general, comparable to those reported for unswept wings. The longitudinal stability at the stall was not materially affected at the ground heights of the present tests."
Date: October 1951
Creator: Furlong, G. Chester & Bollech, Thomas V.
Partner: UNT Libraries Government Documents Department

Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons

Description: From Summary: "An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.93 to determine the effects on the chordwise pressure distributions of projecting various spoiler-type ailerons on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6. The results of the investigation are presented as curves of chordwise pressure distributions near the midspan of the spoilers (0.46-wing-semispan station)."
Date: June 24, 1952
Creator: Hammond, Alexander D. & McMullan, Barbara M.
Partner: UNT Libraries Government Documents Department

Theoretical lift and damping in roll at supersonic speeds of thin sweptback tapered wings with streamwise tips, subsonic leading edges, and supersonic trailing edges

Description: "On the basis of linearized supersonic-flow theory, generalized equations were derived and calculations made for the lift and damping in roll of a limited series of thin sweptback tapered wings. Results are applicable to wings with streamwise tips and for a range of supersonic speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and from the trailing edge of the root section. A further limitation is that the tip Mach lines may not intersect on the wing" (p. 395).
Date: February 15, 1949
Creator: Malvestuto, Frank S., Jr.; Margolis, Kenneth & Ribner, Herbert S.
Partner: UNT Libraries Government Documents Department

Theoretical calculations of the lateral force and yawing moment due to rolling at supersonic speeds for sweptback tapered wings with streamwise tipssupersonic leading edges

Description: Report presenting theoretical results for the lateral force and yawing moment due to combined angle of attack and roll. The thin wings are tapered and have leading and trailing edges which are each swept at a constant angle; the tips are parallel to the center section.
Date: July 1950
Creator: Harmon, Sidney M. & Martin, John C.
Partner: UNT Libraries Government Documents Department

Comparison of experimental with calculated results for the lifting effectiveness of a flexible 45 degree sweptback wing of aspect ratio 6.0 at Mach numbers from 0.8 to 1.3

Description: Report presenting tests conducted on models with 45 degree sweptback wings with varying degrees of flexibility to determine the effective lift-curve slopes in order to evaluate the usefulness of a general method for predicting effective lift ratio by a comparison of predicted values with test results.
Date: April 15, 1954
Creator: Walters, Richard E.
Partner: UNT Libraries Government Documents Department

Results of a flight investigation to determine the zero-lift drag characteristics of a 60 degree delta wing with NACA 65-006 airfoil section and various double-wedge sections at Mach numbers from 0.7 to 1.6

Description: Report presenting results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models with 60 degree sweptback delta wings presented for a range of Mach numbers. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness.
Date: April 1956
Creator: Welsh, Clement J.
Partner: UNT Libraries Government Documents Department

Analysis of Pure-Bending Flutter of a Cantilever Swept Wing and Its Relation to Bending-Torsion Flutter

Description: From Introduction: "The present paper is intended to give some features of flutter in bending alone and contains results of analyses made to determine some effects of wing mass-density ratio, angle of sweepback, length-semichord ratio, and Mach number. Some relations of pure-blending flutter to the conventional bending-torsion flutter are also given."
Date: September 1951
Creator: Cunningham, H. J.
Partner: UNT Libraries Government Documents Department

Effect of Sweepback and Aspect Ratio on Longitudinal Stability Characteristics of Wings at Low Speeds

Description: Note presenting an analysis of the available data on the longitudinal stability characteristics of sweptback wings at low speeds. The analysis indicated that the shape of the pitching-moment curve near the stall for sweptback wings is greatly dependent on the aspect ratio. The addition of a horizontal tail behind the wings may be destabilizing and requires further investigation.
Date: July 1946
Creator: Shortal, Joseph A. & Maggin, Bernard
Partner: UNT Libraries Government Documents Department