UNT Libraries Government Documents Department - 143 Matching Results

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An Empirical Method Permitting Rapid Determination of the Area, Rate and Distribution of Water-Drop Impingement on an Airfoil of Arbitrary Section at Subsonic Speeds

Description: "An empirical method for the determination of the area, rate, and distribution of water-drop impingement on airfoils of arbitrary section is presented. The procedure represents an initial step toward the development of a method which is generally applicable in the design of thermal ice-prevention equipment for airplane wing and tail surfaces. Results given by the proposed empirical method are expected to be sufficiently accurate for the purpose of heated-wing design, and can be obtained from a … more
Date: September 1951
Creator: Bergrun, Norman R.
Item Type: Refine your search to only Report
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An Instrument Employing a Coronal Discharge for the Determination of Droplet-Size Distribution in Clouds

Description: From Summary: "A flight instrument that uses electric means for measuring the droplet-size distribution in above-freezing clouds has been devised and given preliminary evaluation in flight. An electric charge is placed on the droplets and they are separated aerodynamically according to their mass. Because the charge placed on the droplets is a. function of the droplet size, the size spectrum can 'be determined by measurement of the charge deposited on cylinders of several different sizes placed… more
Date: September 1951
Creator: Brun, Rinaldo J.; Levine, Joseph & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
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Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

Description: "A cascade impactor, an instrument for obtaining the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor" (p. 1).
Date: September 18, 1951
Creator: Levine, Joseph & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
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Comparison of Heat Transfer from Airfoil in Natural and Simulated Icing Conditions

Description: "An investigation of the heat transfer from an airfoil in clear air and in simulated icing conditions was conducted in the NACA Lewis 6- by 9-foot icing-research tunnel in order to determine the validity of heat-transfer data as obtained in the tunnel. This investigation was made on the same model NACA 65,2-016 airfoil section used in a previous flight study, under similar heating, icing, and operating conditions. The effect of tunnel turbulence, in clear air and in icing was indicated by the f… more
Date: September 1951
Creator: Gelder, Thomas F. & Lewis, James P.
Item Type: Refine your search to only Report
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A General Correlation of Temperature Profiles Downstream of a Heated-Air Jet Directed Perpendicularly to an Air Stream

Description: "An experimental investigation was conducted to determine the temperature profile downstream of a heated-air jet directed perpendicularly to an air stream. The profiles were determined at several positions downstream of the jet as functions of jet density, jet velocity, free-stream density, free-stream velocity, jet temperature, and orifice flow coefficient. A method is presented which yields a good approximation of the temperature profile in terms of dimensionless parameters of the flow and ge… more
Date: September 1951
Creator: Callaghan, Edmund E. & Ruggeri, Robert S.
Item Type: Refine your search to only Report
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Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine. 7: Rotor-Blade Fabrication Procedures

Description: "An experimental investigation was conducted to determine the cooling effectiveness of a wide variety of air-cooled turbine-blade configurations. The blades, which were tested in the turbine of a - commercial turbojet engine that was modified for this investigation by replacing two of the original blades with air-cooled blades located diametrically opposite each other, are untwisted, have no aerodynamic taper, and have essentially the same external profile. The cooling-passage configuration is … more
Date: September 12, 1951
Creator: Long, Roger A. & Esgar, Jack B.
Item Type: Refine your search to only Report
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Calculated Performance of a Mercury-Compressor-Jet Powered Airplane Using a Nuclear Reactor as an Energy Source

Description: Memorandum presenting an analysis of a system consisting of a mercury turbine-driven air compressor a mercury condenser wherein heat was added to the compressed air. The heat addition to the mercury is accomplished in an intermediate heat exchanger (mercury boiler) which has a liquid metal, other than mercury, circulating through the opposite side and through a nuclear reactor. Results regarding the turbine-exhaust pressure, turbine-inlet pressure, condenser-inlet Mach number, effect of nacelle… more
Date: September 26, 1951
Creator: Doyle, R. B.
Item Type: Refine your search to only Report
open access

Measurement of distortion in second experimental control rod for argonne naval reactor with constant transverse temperature gradient and uniform longitudinal temperature distribution

Description: Report presenting measurements of the thermal distortion of a stainless-steel clad, cadmium-silver reactor control rod. The temperature pattern of the rod is described. The maximum reduction in clearance obtained in the tests was 0.203 inch.
Date: September 26, 1951
Creator: Nagey, T. F. & Lietzke, A. F.
Item Type: Refine your search to only Report
open access

Analytical method for determining performance of turbojet-engine tail-pipe heat exchangers

Description: From Introduction: "The NACA Lewis laboratory has undertaken a program of analytical study to evaluate the effect on turbojet-engine performance of extracting energy from several points in the cycle. The program included an investigation of the effects of air bleed from the compressor outlet, hot gas bleed from the turbine inlet, hot gas bleed from the turbine outlet, and shaft power extraction (references 1 to 4). "
Date: September 1951
Creator: Behun, Michael & Chandler, Harrison C., Jr.
Item Type: Refine your search to only Report
open access

Effect of an autopilot sensitive to yawing velocity on the lateral stability of a typical high-speed airplane

Description: Report presenting a theoretical investigation to determine the effect on the lateral stability of a typical high-speed fighter airplane of an autopilot sensitive to yawing velocity. The effects of inclination of the gyro spin axis to the flight path and of time lag in the autopilot were also determined. The damping of lateral oscillation of the airplane for all flight conditions studied should satisfy the Air Force-Navy criterion when the proposed autopilot is installed.
Date: September 1951
Creator: Gates, Ordway B., Jr. & Sternfield, Leonard
Item Type: Refine your search to only Report
open access

Jet-boundary corrections for complete and semispan swept wings in closed circular wind tunnels

Description: Report presenting tables and curves that give values of the induced-upwash-velocity factors, due to jet boundary, at the horizontal center plane of a closed circular wind tunnel and of a closed bipolar wing tunnel. The application of induced-upwash-velocity factors to the determination of jet-boundary corrections is also discussed.
Date: September 1951
Creator: Sivells, James C. & Salmi, Rachel M.
Item Type: Refine your search to only Report
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A Method of Designing Turbomachine Blades With a Desirable Thickness Distribution for Compressible Flow Along an Arbitrary Stream Filament of Revolution

Description: Note presenting a rapid method for designing turbomachine blades of a given turning and a desirable blade-thickness distribution for a compressible non-viscous fluid flow along an arbitrary stream filament of revolution. The method is illustrated with the design of several turbine cascades of highly cambered thick blades.
Date: September 1951
Creator: Wu, Chung-Hua & Brown, Curtis A.
Item Type: Refine your search to only Report
open access

Width of Debye-Scherrer Lines for Finite Spectral Width of Primary Beam

Description: "The width of a Debye-Scherrer line under the combined influence of spectral width of the primary radiation and of the small size of the crystal grains is calculated, omitting all geometric causes of line broadening. The shape of the crystals is assumed spherical, with the same diameter for all grains. The orientation is assumed to be random, with negligible statistical fluctuations" (p. 1).
Date: September 1951
Creator: Ekstein, Hans
Item Type: Refine your search to only Report
open access

X-Ray Diffraction by Bent Crystal Lamellae

Description: Note presenting an overview of bent crystal lamellae, which may consist of individual blocks, spaced somewhat irregularly and with a mutual angular disorientation. In this case, the x-ray intensities of the individual blocks will simply be added. A study was done to determine if there was any difference between diffraction by a bent lamella and by an array of irregularly spaced blocks arranged in a circle.
Date: September 1951
Creator: Ekstein, Hans
Item Type: Refine your search to only Report
open access

Method of matching components and predicting performance of turbine-propeller engine

Description: Report presenting equations derived for the equilibrium operation of a turbine-propeller engine in terms of parameters used in turbine- and compressor-performance maps. By use of the analytical relations, geometric, thermodynamic, and aerodynamic relations among compressor, turbine, and exhaust nozzle may be calculated.
Date: September 1951
Creator: Sutor, Alois T. & Zipkin, Morris A.
Item Type: Refine your search to only Report
open access

Flight Investigation of Some Factors Affecting the Critical Tail Loads on Large Airplanes

Description: Note presenting an investigation of the maneuvering tail load requirements conducted using a Lockheed Constitution airplane. An analysis of the forces exerted by the pilot, the control motions, and the airplane responses for a series of maneuvers occurred. Results regarding pitching maneuvers, yawing maneuvers, rolling pull-outs, and structural deflections are provided.
Date: September 1951
Creator: Brown, Harvey H.
Item Type: Refine your search to only Report
open access

A method of solving the direct and inverse problem of supersonic flow along arbitrary stream filaments of revolution in turbomachines

Description: Report presenting an analysis of the supersonic flow in two two-dimensional high-solidity cascades and in a partly supersonic symmetrical nozzle. A method is developed for the determination of the supersonic flow along stream surfaces of revolution in turbomachines. In addition to their use in direct problems, the equations can be used to design blade elements in supersonic flow along an arbitrary stream filament of revolution in turbomachines.
Date: September 1951
Creator: Wu, Chung-Hua & Costilow, Eleanor L.
Item Type: Refine your search to only Report
open access

Generalized conical-flow fields in supersonic wing theory

Description: Report presenting linearized, compressible flow analysis as applied to the study of quasi-conical supersonic wing theory. Single-integral equations are derived which relate either the loading to the shape of a lifting surface or the thickness of a symmetrical wing to the pressure distribution for triangular wings with subsonic leading edges. For the nonlifting case, it is shown that for a specified pressure distribution the theory does not always predict a unique thickness distribution.
Date: September 1951
Creator: Lomax, Harvard & Heaslet, Max A.
Item Type: Refine your search to only Report
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