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Exploratory investigation at high and low subsonic Mach numbers of two experimental 6-percent-thick airfoil sections designed to have high maximum lift coefficients

Description: Report presenting an investigation to determine if thin airfoils with increased values of low-speed maximum lift coefficient but also retain the basic advantages of thin sections at high Mach numbers can be developed. Several experimental thin airfoil sections were developed from an analysis of airfoil data and two of them were investigated at high and low subsonic Mach numbers. Results regarding the low-speed characteristics and high-speed characteristics are provided.
Date: December 14, 1951
Creator: Loftin, Laurence K., Jr. & von Doenhoff, Albert E.
Partner: UNT Libraries Government Documents Department

Data presentation of force characteristics of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0

Description: Investigation to determine lift, drag, and pitching-moment characteristics of several engine-strut-body combinations was conducted over range of angles of attack from 0 degrees to 10 degrees at Mach numbers of 1.8 and 2.0. The average Reynolds number based on body length was 28x106. Data are presented without analysis and indicate decreases in minimum drag and lift curve slope with decreasing in minimum drag and lift curve slope with decreasing strut length. Decreases in minimum drag also noted with rear-ward movement of engines.
Date: August 14, 1951
Creator: Madden, Robert T. & Kremzier, Emil J.
Partner: UNT Libraries Government Documents Department

Wind-tunnel tests of a 1/12-scale model of the X-3 airplane at subsonic and supersonic speeds.

Description: Report presenting the static longitudinal-, lateral-, and directional-stability and control characteristics of a model of the Douglas X-3 airplane at subsonic and supersonic Mach numbers. The model was equipped with an all-movable horizontal tail, an aileron on the left wing, and a rudder on the vertical-tail surface.
Date: September 14, 1951
Creator: Olson, Robert N. & Chubb, Robert S.
Partner: UNT Libraries Government Documents Department

Basic pressure measurements on a fuselage and a 45 degrees sweptback wing-fuselage combination at transonic speeds in the slotted test section of the Langley 8-foot high-speed tunnel

Description: Report presenting the first results of pressure measurements obtained on a fuselage and a 45 degree sweptback wing-fuselage combination at transonic speeds in the slotted test section of the 8-foot high-speed tunnel. The test was part of a systematic investigation of varying amounts of sweepback on wings suitable for transonic flight. Results regarding the wing, fuselage, and fuselage with wing are provided.
Date: September 14, 1951
Creator: Loving, Donald L. & Williams, Claude V.
Partner: UNT Libraries Government Documents Department

Effects of horizontal-tail position, area, and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degrees triangular-wing model having various triangular-all-movable horizontal tails

Description: Report presenting a low-speed investigation in the stability tunnel to determine the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with various triangular-all-movable horizontal tails. An all-movable trail of 10 percent of the wing area and aspect ratio 2.31 was investigated in 17 tail positions, including positions above, below, and to the rear of the assumed center of gravity.
Date: December 14, 1951
Creator: Jaquet, Byron M.
Partner: UNT Libraries Government Documents Department

Preliminary Transient Performance Data for Afterburner Operation of Westinghouse Electronic Power Regulator on XJ34-WE-32 Turbojet Engine in Altitude Wind Tunnel

Description: "At the request of the Bureau of Aeronautics, Department of the Navy, an investigation of the Westinghouse XJ34-WE-32 turbojet engine is being conducted in the NACA Lewis altitude wind tunnel to determine the steady-state and transient operating characteristics of the controlled and uncontrolled engine at various altitudes and ram pressure ratios. As part of this program, transient performance data that illustrate the operation of the engine is obtained in the form of oscillographic traces. Similar data for engine operation in the afterburning range, covering a range of throttle settings from the minimum value giving rated speed (throttle position, 72 degrees) to full afterburning (throttle position, 110 degrees), is presented herein" (p. 1).
Date: February 14, 1951
Creator: Vasu, George; Schwent, Glennon V. & Ketchum, James R.
Partner: UNT Libraries Government Documents Department

Note on flutter of a 60 degree delta wing encountered at low-supersonic speeds during the flight of a rocket-propelled model

Description: From Summary: "An analysis of the flight time history of a rocket-propelled model of a 60 degree delta-wing airplane configuration, fired for the purpose of obtaining zero-lift drag data, indicated wing flutter and subsequent failure at low-supersonic Mach numbers. This flutter occurred during the unpowered decelerating portion of the flight. The behavior of the model during flight is discussed and the mass and stiffness characteristics of a duplicate wing are presented."
Date: May 14, 1951
Creator: Lauten, William T., Jr. & Mitcham, Grady L.
Partner: UNT Libraries Government Documents Department

Wing-on and wing-off longitudinal characteristics of an airplane configuration having an thin unswept tapered wing of aspect ratio 3, as obtained from rocket-propelled models at Mach numbers from 0.8 to 1.4

Description: Report presenting flight tests at Mach numbers from 0.8 to 1.4 on three rocket-propelled general research models of airplane configurations. Two models had thin unswept tapered wings of aspect ratio 3 and hexagonal airfoil sections, two wings had different structural stiffness characteristics, and the third model had no wing. Results regarding the static and dynamic longitudinal stability, control, trim, and drag characteristics are provided.
Date: March 14, 1951
Creator: Gillis, Clarence L. & Vitale, A. James
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of the Supersonic Flow Field Downstream of Wire-Mesh Nozzles in a Constant-Area Duct

Description: "An investigation was conducted in a 3.4- by 3.4-inch duct to determine the characteristics of the supersonic flow downstream of four wire-mesh screen nozzles with nominal design Mach numbers in the range between 1.97 and 2.58. Two types of disturbances were observed in the flow field: a fine network of interacting expansion and compression waves which were formed immediately downstream of the screens and appeared to dissipate within 25 to 40 wave intersections; and relatively strong oblique shock waves that originated at the junctions of the screens and the walls and were reflected throughout the length of the duct. Regions of fairly uniform flow were found to exist" (p. 1).
Date: August 14, 1951
Creator: Gould, Lawrence I.
Partner: UNT Libraries Government Documents Department

Supersonic Tunnel Investigation by Means of Inclined-Plate Technique to Determine Performance of Several Nose Inlets Over Mach Number Range of 1.72 to 2.18

Description: Memorandum presenting a study using a suspended flat plate to continuously vary the Mach number in the 18- by 18-inch Mach number 1.91 supersonic tunnel. The technique was applied to the determination of pressure recovery and mass-flow characteristics of four supersonic nose inlets over the Mach number range produced. Results regarding the plate calibration and inlet performance are provided.
Date: February 14, 1951
Creator: Fox, Jerome L.
Partner: UNT Libraries Government Documents Department

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 3: conical-spike all-external-compression inlet with supersonic cowl lip

Description: Memorandum presenting an investigation conducted in the Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet with a conical spike and a supersonic cowl lip. Measurements of lift, drag, pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees.
Date: February 14, 1951
Creator: Weinstein, Maynard I. & Davids, Joseph
Partner: UNT Libraries Government Documents Department

Notes on Heat-Resistant Materials in Britain from Technical Mission October 13 to November 30, 1950

Description: Memorandum presenting a summary of heat-resistant materials obtained from interviews with alloy producers, jet-engine manufacturers, and research laboratories in Britain during October and November 1950. The primary subjects of interest included the properties of materials and service requirements for gas turbines, criteria used for judging and inspecting materials, and research developments of both a practical and fundamental nature in the field.
Date: May 14, 1951
Creator: Freeman, J. W. & Cross, Howard C.
Partner: UNT Libraries Government Documents Department

Description and Investigation of a Dynamic Model of the XH-17 Two-Blade Jet Driven Helicopter

Description: Report presenting a description and results of an investigation of a model of the XH-17 two-blade, jet-powered helicopter. Tests were made with a standard configuration and with several modifications, including varying the size of blade counterweights, changing the control stiffness and chordwise bending stiffness of the blades, and varying the pylon and undercarriage damping and spring constants. Results regarding flutter testing, ground-vibration tests, and three-per-revolution rotor-blade unsymmetric bending oscillations are provided.
Date: March 14, 1951
Creator: Brooks, George W. & Sylvester, Maurice A.
Partner: UNT Libraries Government Documents Department

Flight Determination of the Effects of Wing Vortex Generators of the Aerodynamic Characteristics of the Douglas D-558-I Airplane

Description: Report presenting testing using a Douglas D-558-I airplane to determine the effect of wing vortex generators on some of the undesirable handling characteristics of aircraft flying at hypercritical speeds. The effects on buffeting, lateral unsteadiness, change in trim, and loss of control effectiveness were the primary objectives.
Date: August 14, 1951
Creator: Beeler, De E.; Bellman, Donald R. & Griffith, John H.
Partner: UNT Libraries Government Documents Department

Time Histories of the Aerodynamic Loads on the Vertical and Horizontal Tail Surfaces of a Jet-Powered Bomber Airplane During Sideslip Maneuvers at Approximately 20,000 Feet

Description: Report presenting time histories of the aerodynamic loads on the vertical and horizontal tail surfaces of a jet-powered bomber airplane (B-45A) in sideslip maneuvers. Information about maximum measured rudder and fin loads, maximum total vertical-tail load, horizontal-tail-load dissymmetry, maximum elevator loads, and elevator-load dissymmetry is provided.
Date: March 14, 1951
Creator: Cooney, T. V. & McGowan, William A.
Partner: UNT Libraries Government Documents Department