National Advisory Committee for Aeronautics (NACA) - 48 Matching Results

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Investigation of the Kingfisher XAUM-2 Flying Torpedo in the Langley Full Scale Tunnel, TED No. NACA DE 327

Description: Report presenting an investigation of a model of the Kingfisher XAUM-2 flying torpedo to determine the pressure recoveries within the jet engine nacelle and to determine the effects of several changes in model configuration on the aerodynamic characteristics of the model. The effectiveness of elevons and tabs as control devices was also investigated.
Date: October 6, 1949
Creator: Cocke, Bennie W. & Barnett, U. Reed
Partner: UNT Libraries Government Documents Department

Flight-test evaluation of the longitudinal stability and control characteristics of 0.5-scale models of the Lark pilotless-aircraft configuration

Description: Report presenting flight tests to determine the longitudinal stability and control characteristics of models of the Lark pilotless aircraft. Testing included the standard configuration with the horizontal wing flaps deflected 0 degrees, 15 degrees, and 60 degrees, and a test with the tail surfaces in line with the wings with the wing flaps not deflected. Results regarding time-history records, drag, longitudinal stability, and control effectiveness are provided.
Date: February 6, 1948
Creator: Stone, David G.
Partner: UNT Libraries Government Documents Department

Location of Detached Shock Wave in Front of a Body Moving at Supersonic Speeds

Description: It is shown that for velocities slightly in excess of sonic, the position of detached shock wave located in front of a given body at zero angle of attack may be estimated theoretically to a reasonable degree of accuracy. In case of bodies of revolution the result was simple, but for two-dimensional bodies, pressure coefficient varies with Mach number, and slight difficulty appears. Theory developed compares favorably with available experimental data.
Date: May 6, 1947
Creator: Laitone, Edmund V. & Pardee, Otway O'm.
Partner: UNT Libraries Government Documents Department

Comparative drag measurements at transonic speeds of an NACA 65-006 airfoil and a symmetrical circular-arc airfoil

Description: Report presenting measurements made at transonic speeds by the freely-falling-body method to compare the drag of a rectangular plan-form airfoil of aspect ratio 7.6 with an NACA 65-006 airfoil section. Results regarding the velocity measurements, base-pressure measurements, and airfoil drag measurements are provided.
Date: March 6, 1947
Creator: Thompson, Jim Rogers & Marschner, Bernard W.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of 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: From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuelage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date: September 6, 1949
Creator: King, Thomas J., Jr. & Myers, Boyd C., II
Partner: UNT Libraries Government Documents Department

An analysis of airspeeds attained by a Douglas DC-4 airplane in commercial operations during the early months of 1947

Description: Report presenting airspeed and altitude data for nonscheduled cargo operations of a Douglas DC-4 airplane between Seattle, Washington and Alaska during February and March of 1947 to determine the probability of reaching or exceeding given values of airspeed and Mach number. The total probability of exceeding a placard never-exceed speed of 266 mph depends primarily on exceeding the speed in descent. The probability was found to be about once in 100 hours of descent or once in 1000 hours of general flying time.
Date: October 6, 1949
Creator: Steiner, Roy
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness

Description: From Introduction: "A 12-percent-chord-thick wedge section and a reversed NACA 0012 section were chosen for these tests as they are representative of sections having no boat tailing and appreciable boat tailing (i.e., blunt and rounded trailing edges, respectively), and the results of this investigation are compared with those obtained from a previous investigation of the NACA 0012 section. Conclusions are drawn regarding the relative merits of the two unconventional sections and the conventional section in transonic speed range."
Date: November 6, 1947
Creator: Eggers, A. J., Jr.
Partner: UNT Libraries Government Documents Department

Properties of certain intermetallics as related to elevated-temperature applications 1: molybdenum disilicide

Description: Report presenting a method for the preparation and purification of the intermetallic molybdenum desilicide was developed and its properties were determined. Chemical properties were found to be highly inert, unattacked by boiling hydrochloric acid, sulfuric acid, or aqueous sodium hydroxide, slightly attacked by nitric acid, and dissolved by molten sodium hydroxide. Other mechanical properties of the material were also provided.
Date: October 6, 1949
Creator: Maxwell, W. A.
Partner: UNT Libraries Government Documents Department

An investigation of the low-speed characteristics of two sharp-edge supersonic inlets designed for essentially external supersonic compression

Description: Report presenting an investigation of two sharp-edge annular inlets with conical central bodies at low airspeeds in the propeller research tunnel to obtain information concerning the surface-pressure, drag, and pressure-recovery characteristics of the inlets at subsonic flight. Results regarding the nose and inner surface of the diffuser, inlet lips, minimum surface pressures and critical Mach numbers, pressure surveys in inlets, and pressure surveys in diffusers are provided.
Date: June 6, 1947
Creator: Dennard, John S.
Partner: UNT Libraries Government Documents Department

The effect of blade-section thickness ratios on the aerodynamic characteristics of related full-scale propellers at Mach numbers up to 0.65

Description: Report discussing an investigation of two full-scale NACA propellers at a range of blade angles and at speeds of up to 500 miles per hour. The results are compared to previous investigations of five NACA propellers to evaluate the effects of blade-section thickness ratios on propeller characteristics.
Date: June 6, 1949
Creator: Maynard, Julian D. & Steinberg, Seymour
Partner: UNT Libraries Government Documents Department

Investigation of downwash and wake characteristics at a Mach number of 1.53 2: triangular wing

Description: Report presenting the results of an experimental investigation of the downwash and wake characteristics behind a triangular plan-form wing in a supersonic stream. Measurements were made of the variation of downwash angle with angle of attack at several positions within the induced flow field. Results regarding the spanwise variation of the induced stream angle, rate of change of downwash at zero lift, variation of downwash with angle of attack, and wake are provided.
Date: June 6, 1949
Creator: Perkins, Edward W. & Canning, Thomas N.
Partner: UNT Libraries Government Documents Department

Some pressure-distribution measurements on a swept-wing at transonic speeds by the NACA wing-flow method

Description: Report presenting results of chordwise pressure-distribution measurements on a 45 degree sweptback wing at transonic speeds. The two stations for measuring were located at the 18 percent chord from the root and the 87 percent chord. The changes in pressure distribution with Mach number did not indicate any appreciable net loss in section lift, but did indicate large increases in the section drag and diving moment.
Date: June 6, 1947
Creator: Johnston, J. Ford & Danforth, Edward C. B.
Partner: UNT Libraries Government Documents Department

Two-dimensional wind-tunnel investigation of a 6-percent-thick symmetrical circular-arc airfoil section with leading-edge and trailing-edge high-lift devices deflected in combination

Description: Report presenting a two-dimensional wind-tunnel investigation of a 6-percent-thick symmetrical circular-arc airfoil with leading-edge and trailing-edge high-lift devices. The purpose of the investigation was to determine the effects on maximum section lift coefficient of different leading-edge slats and drooped-nose flaps when used in combination with a plain trailing-edge flap. Results regarding slat configuration, drooped-nose-flap configurations, and a comparison of slat and drooped-nose-flap configurations are provided.
Date: September 6, 1949
Creator: Nuber, Robert J. & Cheesman, Gail A.
Partner: UNT Libraries Government Documents Department

Experimental investigation of thrust augmentation of a turbojet engine at zero ram by means of tail-pipe burning

Description: Report presenting an investigation of the performance of a turbojet engine equipped with a tail-pipe burner at zero ram over a range of rotor speeds and tail-pipe-burner fuel flows. A thrust augmentation of 40 percent was obtained at zero ram for a tail-pipe-burner fuel-air ratio of 0.043 or a total fuel-air ratio of 0.056. Results with an engine with standard tail pipe, engine with tail pipe burner and no afterburning, and engine with tail pipe burner and afterburning are provided.
Date: January 6, 1947
Creator: Lundin, Bruce T.; Dowman, Harry W. & Gabriel, David S.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Low-Speed Static Stability and Control Characteristics of a Model of Bell MX-776

Description: An investigation has been made in the Langley stability tunnel to determine the low-speed static stability and control characteristics of a model of the Bell MX-776. The results of the investigation indicated that the basic model configuration was longitudinally stable in the angle-of-attack range from about -16 deg. to 16 deg. but that the stability was a minimum near O deg angle of attack. The data indicated an aerodynamic-center position about 0.64 body diameters behind the center of gravity at low angles of attack. Reduction in the size of the front horizontal fins increased the longitudinal stability. With 20 percent of the span of the normal front horizontal fins cut off the aerodynamic center was about 1.04 body diameters behind the center of gravity, and with front horizontal fins having the same area as the front vertical fins, the aerodynamic center was 2.26 body diameters behind the center of gravity (at low angles of attack).
Date: July 6, 1949
Creator: Queijo, M. J. & Michael, W. H., Jr.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine. 2 - Operational Characteristics

Description: From Summary: "An investigation was conducted in the Cleveland altitude wind tunnel to determine the operational characteristics of an axial flow-type turbojet engine with a 4000-pound-thrust rating over a range of pressure altitudes from 5,000 to 50,000 feet, ram pressure ratios from 1.00 to 1.86, and temperatures from 60 deg to -50 deg F. The low-flow (standard) compressor with which the engine was originally equipped was replaced by a high-flow compressor for part of the investigation. The effects of altitude and airspeed on such operating characteristics as operating range, stability of combustion, acceleration, starting, operation of fuel-control systems, and bearing cooling were investigated."
Date: August 6, 1948
Creator: Fleming, William A.
Partner: UNT Libraries Government Documents Department

Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) 1: longitudinal stability and control characteristics

Description: Report discussing testing of the Douglas A-26B to determine the longitudinal stability and control characteristics. Information about the elevator, stick-fixed and stick-free stability, center of gravity, and flap effects are described.
Date: December 6, 1944
Creator: Crane, H. L.; Sjoberg, S. A. & Hoover, H. H.
Partner: UNT Libraries Government Documents Department

Effect of Mach and Reynolds numbers on the maximum lift coefficient obtainable in gradual and abrupt stalls of a pursuit airplane equipped with a low-drag wing

Description: Report discussing flight tests on a low-drag wing pursuit airplane to determine the effects of Mach and Reynolds numbers on the maximum lift coefficient obtainable in gradual and abrupt stalls. The obtainable maximum lift coefficient was found to be greatly affected by the Mach and Reynolds numbers in gradual stall. In abrupt stalls, the maximum lift coefficient was affected by the Mach number, but not the Reynolds number.
Date: July 6, 1945
Creator: Spreiter, John R.; Galster, George M. & Blair, William K.
Partner: UNT Libraries Government Documents Department