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

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The Effect of Changing the Ratio of Exhaust-Valve Flow Capacity to Inlet-Valve Flow Capacity on Volumetric Efficiency and Output of a Single-Cylinder Engine

Description: Report presenting a series of tests with a single-cylinder engine in order to determine the effect on volumetric efficiency and on engine performance of changing the ratio of exhaust-valve flow capacity to inlet-valve flow capacity when operating with exhaust pressure equal to inlet pressure.
Date: October 1947
Creator: Eppes, James V. D.; Livengood, James C. & Taylor, C. Fayette
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Limits of Precision in the Determination of Lattice Parameters and Stresses by the Debye-Scherrer Method

Description: Note an investigation regarding the limits of precision in the determination of lattice parameters. Experiments were performed with copper radiation on zinc samples. Even when the crystal-grain orientation is perfectly uniform, the recording of the intensity distribution will entail errors.
Date: October 1947
Creator: Ekstein, Hans & Siegel, Stanley
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Spot Welding of Dissimilar Aluminum Alloys in the 0.040-Inch Thickness

Description: Note presenting an investigation of the spot welding of eight dissimilar alloy combinations in 0.40-inch thickness as part of a program on aircraft spot-welding. The results indicate that in many instances, the chemical treatment of dissimilar alloys prior to spot welding is a less difficult problem than the treatment of some similar alloy combinations. They also indicated that all of the combinations can be spot-welded with little difficulty.
Date: October 1947
Creator: Hess, W. F.; Wyant, R. A. & Winsor, F. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Friction at high sliding velocities

Description: Report presenting information that extends the range of existing fundamental friction knowledge to include sliding velocities encountered in rolling-contact bearings and reduction gears of aircraft power plants. Experiments were conducted with a kinetic-friction apparatus consisting basically of an elastically restrained spherical rider sliding on a dry or lubricated rotating disk. The results indicate that the kinetic friction decreases with sliding speed for dry and for some boundary-lubricat… more
Date: October 1947
Creator: Johnson, Robert L.; Swikert, Max A. & Bisson, Edmond E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Impact Theory for Seaplane Landings

Description: Note presenting an analysis of a step landing of a seaplane on smooth water by solving Newton's differential equation of motion. Formulas are developed for the maximum acceleration, the maximum draft, and the draft at the instant of maximum acceleration.
Date: October 1947
Creator: Benscoter, Stanley U.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of variation in diameter and pitch of rivets on compressive strength of panels with Z-section stiffeners panels of various stiffener spacings that fail by local buckling

Description: Report presenting an investigation conducted to determine the effect of varying the rivet diameter and pitch on the compressive strength of flat 24S-T aluminum-alloy Z-stiffened panels of the type for which design charts are available. The primary focus of the investigation is concerned with panels which have the smallest values of width-to-thickness ratio of the webs of the stiffeners given by the design charts and have such length that failure is by local buckling.
Date: October 1947
Creator: Dow, Norris F. & Hickman, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-speed static stability and damping-in-roll characteristics of some swept and unswept low-aspect-ratio wings

Description: Report presenting an investigation at low speed to determine static stability and damping-in-roll characteristics of a number of low-aspect-ratio wings, including swept wings of approximately triangular plan form, in the free-flight and 15-foot free-spinning tunnels. Static longitudinal stability, directional stability, effective dihedral, and damping in roll are provided.
Date: October 1947
Creator: Tosti, Louis P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of NACA 65(sub 112) A111 (approx.) airfoil with 0.35-chord slotted flap at Reynolds numbers up to 25 million

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnel and low-turbulence pressure tunnel to determine the highest maximum lift configurations of a slotted flap on an NACA 65(sub 112)A111 (approx.) airfoil section. The scale effects on aerodynamic characteristics were determined for a range of Reynolds numbers. Results regarding flap configurations, lift characteristics, pitching-moment characteristics, drag characteristics, and effects of leading-edge roughness are pro… more
Date: October 1947
Creator: Racisz, Stanley F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical and Experimental Investigation of Bolted Joints

Description: From Introduction: "The present paper contains the development of a recurrence formula for the bolt loads for the simplified case of a symmetrical butt joint with bolts spaced evenly in line with the applied load. The method presented herein is based on the fundamental relationship which was developed in reference 1 between the loads on any two successive bolts. The present paper also gives the results of an experimental investigation conducted to substantiate further the adequacy of the elasti… more
Date: October 1947
Creator: Rosenfeld, Samuel J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Performance of Jet Engine From Characteristics of Components 1: Aerodynamic and Matching Characteristics of Turbine Component Determined With Cold Air

Description: Note presenting the performance of the turbine component of a research jet engine investigated with cold air. The interaction and matching of the turbine with the eight-stage compressor were computed with the combination considered as a jet engine and overall performance of the engine was then determined. Results regarding the performance of the first stator ring, turbine performance, and turbine-compressor matching are provided.
Date: October 1947
Creator: Goldstein, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Effects of Unsymmetrical Horizontal-Tail Arrangements on Power-on Static Longitudinal Stability of a Single-Engine Airplane Model

Description: Report presenting a wind-tunnel investigation to determine the effects of unsymmetrical horizontal-tail arrangements on the power-on static longitudinal stability of a single-engine single-rotation airplane. Extreme asymmetry in the horizontal tail was found to cause issues with the longitudinal stability, but the "practical" arrangement tested did not show much improvement. Results regarding the longitudinal stability tests, computations, and lateral and directional trim are provided.
Date: October 1947
Creator: Purser, Paul E. & Spear, Margaret F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Generalized Performance Comparison of Large Conventional, Tail Boom, and Tailless Airplanes

Description: Report presenting an investigation to determine the performance of large tailless and conventional airplanes. The primary conclusion drawn fro the testing is that large all-wing tailless airplanes may have better performance characteristics than their equivalent tail-boom airplanes for certain types of missions. Results regarding a general performance comparison, performance variations with structural weight, landing speed, and take-off distance, and performance comparison based on arbitrary de… more
Date: October 1947
Creator: Ankenbruck, Herman O. & McKinney, Marion O., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-Layer Momentum Equations for Three-Dimensional Flow

Description: Note presenting boundary-layer momentum equations for the three-dimensional flow of a fluid with variable density and viscosity in a form similar to the momentum equation for two-dimensional flow. The momentum equations can be reduced to the forms of the three-dimensional momentum equations that have been given recently by Prandtl for a fluid with constant density and viscosity.
Date: October 1947
Creator: Tetervin, Neal
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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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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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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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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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Characteristics of a 15-Percent-Chord and a 35-Percent-Chord Plain Flap on the NACA 0006 Airfoil Section at High Subsonic Speeds

Description: Memorandum presenting wind-tunnel tests to determine the aerodynamic characteristics of a 15-percent- and a 35-percent-chord plain trailing-edge flap on the NACA 0006 airfoil section. Simultaneous measurements of section lift, drag, and pitching moment were made over a range of Mach numbers, angles of attack, and flap deflections.
Date: October 2, 1947
Creator: Ilk, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Sample Size on the Determination of Maximum Gust Velocities in Clouds

Description: Report presenting the application of simple sampling procedures to gust data obtained from P-61 thunderstorm flights in Orlando, Florida. The results demonstrated that the observed values of maximum effective gust velocities tend to be functions of the record distance of cloud survey.
Date: October 10, 1947
Creator: Press, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Airspeeds and Mach Numbers Attained by Lockheed Constellation Airplanes in Transcontinental Operations During the Early Summer of 1946

Description: Report presenting airspeed and altitude data obtained from Lockheed Constellation airplanes flying between New York and San Francisco during May and June of 1946 in order to determine the probability of reaching or exceeding given values of airspeed and Mach number. Analysis indicated that the total probability of exceeding the placard "never extend" speed depends primarily on the probability of exceeding this speed in descent. The probability of exceeding the critical Mach number is very negli… more
Date: October 10, 1947
Creator: Steiner, Roy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of performance and operating characteristics of a tail-pipe burner for a turbojet engine

Description: Report presenting an investigation to obtain fundamental information required for the design of a satisfactory tail-pipe burner for augmenting turbojet engine thrust. Investigations were also conducted to determine the combustion and pressure-drop characteristics of the most satisfactory burner, to develop a method of controlling the burner-outlet temperature distribution, and to improve the burner ignition characteristics.
Date: October 30, 1947
Creator: Gabriel, David S.; Martinson, E. Vincent & Essig, Robert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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