National Advisory Committee for Aeronautics (NACA) - 1,172 Matching Results

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Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53

Description: Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale … more
Date: June 24, 1958
Creator: Oehman, Waldo I. & Turner, Kenneth L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hydrodynamic Characteristics of Missiles Launched Under Water

Description: Report presenting some of the hydrodynamic problems associated with launching an air missile from underwater. The results of an experiment with models are also provided, including deviation angle, effect of forward speed of the submarine, curved path of the missile, and potential environmental disruptions.
Date: June 27, 1958
Creator: Dawson, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-Scale Evaluation of Some Flameholder Design Concepts for High-Inlet-Velocity Afterburners

Description: Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.
Date: June 28, 1956
Creator: Prince, William R.; Velie, Wallace W. & Braithwaite, Willis M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical Investigation of Fuel-Cooled Turbine Blades With Return-Flow Type of Finned Coolant Passages

Description: Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen… more
Date: June 26, 1957
Creator: Nachtigall, Alfred J. & Slone, Henry O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine

Description: Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.
Date: June 12, 1957
Creator: Stepka, Francis S.; Richards, Hadley T. & Hickel, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds

Description: "The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).
Date: June 27, 1955
Creator: Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51

Description: Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
Date: June 23, 1958
Creator: Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0

Description: Memorandum presenting an investigation to determine the internal flow performance of a fixed 14 degree ramp inlet from zero to 20 degrees angle of attack conducted at three free-stream Mach numbers. The inlet was mounted in three circumferential fuselage locations and utilized inlet throat and fuselage boundary-layer removal.
Date: June 26, 1957
Creator: Mitchell, Glenn A. & Chiccine, Bruce G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Roll Effectiveness of a Differentially Deflected Horizontal-Tail Surface on a 42 Degree Swept-Wing Model

Description: Memorandum presenting an investigation to determine the roll effectiveness of a differentially deflected horizontal tail of a 42 degree swept-wing model. The model was tested through an angle-of-attack range of 0 degrees through the stall in the clean and landing configurations with the horizontal tail in a low position. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: June 19, 1956
Creator: Boisseau, Peter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Low-Pressure-Loss Short Afterburner for Sea-Level Thrust Augmentation

Description: Memorandum presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.
Date: June 7, 1955
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Transonic and Supersonic Flutter Characteristics of the Upper and Lower Vertical Tails of an Air-to-Ground Missile

Description: "Flutter models of the upper and lower vertical tails of an air-to-ground missile have been tested in the Mach number range from 0.5 to 3.0. It was found that the upper surface exhibited more or less conventional flutter behavior throughout the Mach number range, whereas the lower surface experienced a sudden change in flutter mode at a Mach number of about 1.18. This change in flutter mode was accompanied by a decrease of about 50 percent in the density required for flutter to occur" (p. 1).
Date: June 5, 1957
Creator: Hanson, Perry W. & Rainey, A. Gerald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of JP-4 Fuel With Fluorine-Oxygen Mixtures in 1000-Pound-Thrust Rocket Engines

Description: Memorandum presenting seven injectors of four different types that were tested for use with JP-4-oxygen-fluorine propellant combinations. By using the best of the injectors, high characteristic velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.
Date: June 11, 1958
Creator: Nored, Donald L. & Douglass, Howard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Several Methods of Cyclic De-Icing of a Gas-Heated Airfoil

Description: "Several methods of cyclic de-icing of a gas-heated airfoil were investigated to determine ice-removal characteristics and heating requirements. The cyclic de-icing system with a spanwise ice-free parting strip in the stagnation region and a constant-temperature gas-supply duct gave the quickest and most reliable ice removal. Heating requirements for the several methods of cyclic de-icing are compared, and the savings over continuous ice prevention are shown. Data are presented to show the rela… more
Date: June 22, 1953
Creator: Gray, Vernon H. & Bowden, Dean T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Procedure for the Design of Air-Heated Ice-Prevention Systems

Description: A procedure proposed for use in the design of air-heated systems for the continuous prevention of ice formation on airplane components is set forth. Required heat-transfer and air-pressure-loss equations are presented, and methods of selecting appropriate meteorological conditions for flight over specified geographical areas and for the calculation of water-drop-impingement characteristics are suggested. In order to facilitate the design, a simple electrical analogue was devised which solves th… more
Date: June 1954
Creator: Neel, Carr B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude Performance of a 20-Inch-Diameter Ram-Jet Engine Investigated in a Free-Jet Facility at Mach Number 3.0

Description: Report discussing the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 over a range of simulated altitudes from 60,500 to 66,500 feet. Information about the maximum combustor efficiency, range of exhaust-nozzle total pressures, lean blow-out, diffuser total-pressure recovery, and internal thrust coefficient is provided.
Date: June 15, 1953
Creator: Smolak, George R. & Wentworth, Carl B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Three-Dimensional Instability of Laminar Boundary Layers on Concave Walls

Description: Memorandum presenting a study of the stability of laminar boundary layer profiles on slightly curved walls relative to small disturbances, in the shape of vortices, whose axes are parallel to the principal direction of flow. The result in an eigenvalue problem by which, for a given undisturbed flow at a prescribed wall, the amplification or decay is computed for each Reynolds number and each vortex thickness.
Date: June 1954
Creator: Görtler, H.
Item Type: Refine your search to only Thesis or Dissertation
Partner: UNT Libraries Government Documents Department
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Investigation of Suction-Slot Shapes for Controlling a Turbulent Boundary Layer

Description: Note presenting tests of three types of boundary-layer-control suction slots in a two-dimensional diffuser to investigate design criterions and to evaluate the practical minimum total-pressure losses. Testing occurred at a velocity of about 100 feet per second with a boundary layer with a displacement thickness of 0.85 inch and a shape parameter of about 1.8.
Date: June 1947
Creator: Pierpont, P. Kenneth
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Ice and Frost Formations on Drag of NACA 65(sub 1) -212 Airfoil for Various Modes of Thermal Ice Protection

Description: "The effects of primary and runback icing and frost formations on the drag of an 8-foot-chord NACA 651-212 airfoil section were investigated over a range of angles of attack from 20 to 80 and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.25 to 1.4 grams per cubic meter and datum air temperatures of -30 to 30 F. The results showed that glaze-ice formations, either primary or runback, on the upper surface near the leading edge of the airfoil cau… more
Date: June 1953
Creator: Gray, Vernon H. & von Glahn, Uwe H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation at High Subsonic Speeds of the Rolling-Stability Derivatives of a 1/22 Scale Model of the Republic F-105 Airplane

Description: Report presenting an investigation of the rolling-stability derivatives for a model of the Republic F-105 airplane over a range of Mach numbers and angles of attack. The model retained damping in roll through the test ranges, but values of the damping varied considerably with angles of attack. Derivatives of yawing moment and lateral force due to rolling generally followed previously indicated trends.
Date: June 30, 1955
Creator: Sleeman, William C., Jr. & Hayes, William C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Three Multicylinder Icing Meters and Critique of Multicylinder Method

Description: "Three multicylinder cloud meters, fundamentally similar but differing in important details, were compared in use at the Mount Washington Observatory. Determinations of liquid water content were found to agree within the limits of the probable error, but the two instruments designed by the National Advisory Committee for Aeronautics indicated larger drop sizes than did the Observatory's instrument, apparently because of spurious ice catch on the rather rough surface of the larger cylinders. Com… more
Date: June 1952
Creator: Howell, Wallace E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Penetration of an Air Jet Directed Perpendicularly to an Air Stream

Description: Note presenting an experimental investigation to determine the penetration of a circular air jet directed perpendicularly to an air stream as a function of jet density, jet velocity, air-stream density, air-stream velocity, jet diameter, and distance downstream from the jet. The penetration was determined for nearly constant values of air-stream density at two tunnel velocities, four jet diameters, four positions downstream of the jet, and for a large range of jet velocities and densities.
Date: June 1948
Creator: Callaghan, Edmund E. & Ruggeri, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Observations of Icing Conditions Encountered in Flight During 1948

Description: Note presenting meteorological data from flight observations in icing conditions during the first 5 months of 1948. A total of 335 measurements of liquid-water content and mean-effective drop diameter were obtained by the multicylinder method in the course of 40 flights in icing conditions covering most of the northern United States. Information regarding the discontinuous character of icing clouds, variation of average liquid-water content with extent of icing conditions, and variation of drop… more
Date: June 1949
Creator: Lewis, William & Hoecker, Walter H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Observations on the Method of Determining the Velocity of Airships

Description: To obtain the absolute velocity of an airship by knowing the speed at which two routes are covered, we have only to determine the geographical direction of the routes which we locate from a map, and the angles of routes as given by the compass, after correcting for the variation (the algebraical sum of the local magnetic declination and the deviation).
Date: June 1921
Creator: Volterra, Vito
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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