National Advisory Committee for Aeronautics (NACA) - 4,160 Matching Results

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A Further Investigation of the Meteorological Conditions Conducive to Aircraft Icing

Description: Report presenting meteorological data from flight observations in icing conditions during the winter of 1946-47. Data on liquid water content, temperature, and mean-effective drop diameter are consistent with values previously proposed for maximum icing conditions. Results regarding the icing conditions in altostratus clouds, reexamination of previously proposed design conditions, relation between maximum liquid water content and temperature in layer clouds, typical icing conditions, maximum dr… more
Date: October 1947
Creator: Lewis, William; Kline, Dwight B. & Steinmetz, Charles P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Subsonic flow over thin oblique airfoils at zero lift

Description: Report presenting a report to extend the calculations for pressure distribution over thin oblique airfoils at subsonic speeds. It is found that flows can be obtained by the superposition of elementary conical flow fields. In the case of the sweptback wing, the pressure distributions remain qualitatively similar at subsonic and supersonic speeds.
Date: June 1947
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Laboratory Investigation of Ice Formation and Elimination in the Induction System of a Large Twin-Engine Cargo Aircraft

Description: "The icing characteristics, the de-icing rate with hot air, and the effect of impact ice on fuel metering and mixture distribution have been determined in a laboratory investigation of that part of the engine induction system consisting of a three-barrel injection-type carburetor and a supercharger housing with spinner-type fuel injection from an 18-cylinder radial engine used on a large twin-engine cargo airplane. The induction system remained ice-free at carburetor-air temperatures above 36 F… more
Date: September 1947
Creator: Coles, Willard D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of yawing thin pointed wings at supersonic speeds

Description: From Summary: "An approximate relation is derived for the surface velocity potential of thin pointed wings at supersonic speeds when they are contained within the Mach cone from the vertex. This relation is applied to obtain the pressure distributions, the lift and drag coefficients, the center of pressure, and the rolling moments as a function of angle of yaw for the delta wing. Theoretical curves are presented for a Mach number of the square root of 2 to illustrate the relations."
Date: September 1947
Creator: Evvard, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Changes Found on Run-in and Scuffed Surfaces of Steel Chrome Plate, and Cast Iron

Description: Note presenting a study of run-in and scuffed steel, chrome-plate, and cast-iron surfaces. X-ray and electronic diffraction techniques, micro-hardness determinations, and microscopy were used. The surface changes varied and wer efound to include three classes: chemical reaction, hardening, and crystallite-size alteration.
Date: October 1947
Creator: Good, J. N. & Godfrey, Douglas
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Investigations of the General Instability of Stiffened Metal Cylinders 8: Stiffened Metal Cylinders Subjected to Pure Torsion

Description: "An experimental investigation of the general instability of reinforced thin-walled metal cylinders was carried out at the California Institute of Technology. The basic parameters involved were the spacing and sectional properties of the stiffening elements, the wall thickness, and the diameter of the cylinder. An analysis of the experimental data led to a suitable parameter for estimating the general instability stress of reinforced metal cylinders when subjected to pure torsion loading" (p. 1… more
Date: May 1947
Creator: Dunn, Louis G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts for stress analysis of reinforced circular cylinders under lateral loads

Description: Report presenting charts with coefficients for the stress analysis of a reinforced circular cylinder. They allow for the rapid determination of sheer flows and direct stresses in the sheet of a cylinder as well as the shear forces, axial forces, and bending moments in the rings. Separate charts are also given for three basic ring loadings.
Date: May 1947
Creator: Kempner, Joseph & Duberg, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Boundary Layer and Wake and Their Relation to Airfoil Characteristics - NACA 65(Sub 1)-012 Airfoil With a True Contour Flap and a Beveled-Trailing-Edge Flap

Description: Note presenting two-dimensional flow tests conduced in the 2.5-by 6-foot test section of the stability tunnel on an NACA 65(sub 1)-012 airfoil with a true contour flap and a beveled-trailing-edge flap to determine lift, drag, hinge moment, boundary layer, and wake characteristics. Measurements indicated that the static-pressure gradient through a boundary layer may be large in regions where the airfoil has a small radius of curvature and that a static-pressure rise exists at the vertical positi… more
Date: June 1947
Creator: Mendelsohn, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Simplified Method of Elastic-Stability Analysis for Thin Cylindrical Shells 1: Donnell's Equation

Description: "The equation for the equilibrium of cylindrical shells introduced by Donnell in NACA Technical Report no. 479 to find the critical stresses of cylinders in torsion is applied to find critical stresses for cylinders with simply supported edges under other loading conditions. It is shown that by this method solutions may be obtained very easily and the results in each case may be expressed in terms of two nondimensional parameters, one dependent on the critical stress and the other essentially d… more
Date: June 1947
Creator: Batdorf, S. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of a double-row radial aircraft engine with three methods of safety-fuel injection

Description: Report presenting an investigation to determine whether a safety fuel with a flash point of 122 degrees Fahrenheit could be successfully used in a high-power radial aircraft engine without individual cylinder fuel-injection equipment. The safety fuel was injected into the combustion-air stream in three different ways. Results regarding the standard powers, effect of average fuel-air ratio on mixture distribution, effect of combustion-air temperature on mixture distribution, general engine perfo… more
Date: August 1947
Creator: Michel, Donald J.; Hickel, Robert O. & Voit, Charles H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Studies of Knock-Limited Blending Characteristics of Aviation Fuels 3 - Aromatics and Cycloparaffins

Description: "The knock-limited power at various blend compositions for several aromatics and cycloparaffins individually blended with paraffinic base stocks, as determined in an air-cooled aircraft-engine cylinder at fuel-air ratios of 0.07 and 0.10 is presented. An analysis of the data leads to the conclusion that the extended reciprocal blending relation suggested in a previous NACA report is not generally applicable to such nonparaffinic components, but might possibly be useful as an approximation over … more
Date: August 1947
Creator: Drell, I. L. & Wear, J. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Finite Span on the Airload Distributions for Oscillating Wings 2 - Methods of Calculation and Examples of Application

Description: Note presenting lift and moment distributions calculated for oscillating wings of finite span on the basis of the three-dimensional theory of part I of the report. The results obtained are compared with the corresponding results of the two-dimensional theory.
Date: October 1947
Creator: Reissner, Eric & Stevens, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight tests of a double-hinged horizontal tail surface with reference to longitudinal-stability and control characteristics

Description: Report presenting testing of a double-hinged horizontal tail on a small low-speed airplane to determine the longitudinal stability and control characteristics. The flying characteristics of the airplane equipped with the double-hinged horizontal tail surface were generally satisfactory. The primary effect of removal of the elevator seal was a decrease in the elevator effectiveness.
Date: May 1947
Creator: Hanson, Carl M. & Anderson, Seth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Shear Lag in a Plywood Sheet-Stringer Combination Used for the Chord Member of a Box Beam

Description: "Theoretical and experimental investigations were made of the distribution of strains in a plywood sheet-stringer combination used as the chord member of a box beam acted upon by bending loads. The theoretical solution was obtained with the help of the principle of minimum potential energy and certain simplifying assumptions. Strain measurements were made on a build-up box beam by means of electrical-resistance strain gages connected with strain indicators" (p. 1).
Date: March 1948
Creator: Borsari, Palamede & Yu, Ai-Ting
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of cast aluminum alloys for elevated-temperature service

Description: Report presenting an experimental investigation to develop an aluminum alloy for service at elevated temperatures. The investigation was divided into three parts: (1) The effects of heat treatment and exposure to elevated temperatures on the tensile properties of alloys cooled to room temperature, (2) the effect of alloy additions on the room temperature and elevated-temperature properties of aluminum, 6-percent-magnesium alloys, and (3) the improvement in high-temperature creep properties of s… more
Date: January 1948
Creator: Hodge, Webster; Eastwood, L. W.; Lorig, C. H. & Cross, H. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theory of the Inlet and Exhaust Processes of Internal-Combustion Engines

Description: Note presenting a theory that has been developed for the calculation of the mass of fluid pumped per stroke and of indicator diagrams for the pumping process of internal-combustion engines, compressors, or vacuum pumps. The theory enables the volumetric efficiency and indicator diagrams for the inlet and exhaust processes of an internal-combustion engine to be obtained even before the engine is actually built. It is also possible to calculate some hypothetical inlet and exhaust processes which … more
Date: January 1949
Creator: Tsu, Tsung-Chi
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Performance of a Composite Engine Consisting of a Reciprocating Spark-Ignition Engine, a Blow-Down Turbine, and a Steady-Flow Turbine

Description: Report presenting an analysis of the performance of a composite engine consisting of a reciprocating spark-ignition engine, two superchargers, a blowdown turbine, and a steady-flow turbine. The performance of the configuration was analyzed in order to determine the suitability and cost of design compromises when the size of turbines and superchargers and all gear ratios are assumed fixed. Results regarding the variable-component system, fixed-component system, and auxiliary-propeller system are… more
Date: October 1947
Creator: Turner, L. Richard & Noyes, Robert N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supersonic Wave Drag of Sweptback Tapered Wings at Zero Lift

Description: Note presenting equations derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Results regarding section wave drag and wing wave drag are provided.
Date: October 1947
Creator: Margolis, Kenneth
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical supersonic wave drag of untapered sweptback and rectangular wings at zero lift

Description: Report presenting a theoretical investigation of the supersonic wave drag at zero lift of a series of untapered sweptback wings with thin symmetrical biconvex parabolic-arc sections. The investigation was extended to include Mach numbers which bring the Mach line behind the wing leading edge and also to include wings of rectangular plan form.
Date: October 1947
Creator: Harmon, Sidney M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 26: Development of a Sensitive Plated-Type Thermopile for Measuring Radiation

Description: Report presenting an analysis of the factors determining the power efficiency of radiation thermopiles of the type in which receivers consist of parts of conducts themselves or of coatings or other electrically insulating materials in intimate contact with the conductors. Criterions for maximum power efficiency are calculated for these thermopiles, which can then be applied to general thermopile designs.
Date: July 1948
Creator: Boelter, L. M. K.; Dempster, E. R.; Bromberg, R. & Gier, J. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of temperature distribution and elastic properties of materials on gas-turbine-disk stresses

Description: Report presenting calculations to determine the influence of changes in temperature distribution and elastic material properties on calculated elastic stresses for a typical gas-turbine disk. Severe temperature gradients caused thermal stresses of sufficient magnitude to reduce the operating safety of the disk.
Date: June 1947
Creator: Holms, Arthur G. & Faldetta, Richard D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 27: Distribution of Heat-Transfer Rate in the Entrance Section of a Circular Tube

Description: "Experimental data on the variation of the point unit thermal conductance in the entrance section of a circular tube are presented for 16 different flow conditions of the entering air. Results are compared with values calculated from existing analytical solutions. The average (integrated mean with length) unit thermal conductance is also calculated for eight entering-air conditions and is compared with values resulting from analytical methods" (p. 1).
Date: July 1948
Creator: Boelter, L. M. K.; Young, G. & Iversen, H. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters XXVIII : Equations for Steady-State Temperature Distribution Caused by Thermal Sources in Flat Plates Applied to Calculation of Thermocouple Errors, Heat-meter Corrections, and Heat Transfer by Pin-fin Plates

Description: Report presenting an equation for steady-sate temperature distribution caused by a thermal source (or sink) in a flat plate surrounded on either side by fluids of different temperature and applications for three sections in the report.
Date: August 1948
Creator: Boelter, L. M. K.; Romie, F. E.; Guibert, A. G. & Miller, M. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 29: Comparison of Several Methods of Calculating Heat Losses From Airfoils

Description: Report presenting a critical comparison and summary of the various methods proposed for calculating the unit thermal conductance on the outer surface of a heated wing involving both laminar and turbulent boundary layers, and a new equation is suggested that should indicate the effect of pressure gradient on laminar heat transfer.
Date: October 1948
Creator: Boelter, L. M. K.; Grossman, L. M.; Martinelli, R. C. & Morrin, E. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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