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

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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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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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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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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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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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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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Cooling of gas-turbines 7: effectiveness of air cooling of hollow turbine blades with inserts

Description: Report presenting an analytical investigation to determine primarily the reduction in cooling-air requirement and the increase in effective gas temperature for the same quantity of cooling air resulting from the use of an insert in the cooling-air passage of a hollow air-cooled turbine blade.
Date: October 20, 1947
Creator: Bressman, Joseph R. & Livingood, John N. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Design and performance of family of diffusing scrolls with mixed-flow impeller and vaneless diffuser

Description: A family of diffusing scrolls was designed for use with a mixed-flow impeller and a small-diameter vaneless diffuser. The design theory, intended to maintain a uniform pressure around the scroll inlet, permits determination of the position of scroll cross sections of preassigned area by considering the radial variation in fluid density and the effects of friction along the scroll. Inasmuch as the design method leaves the cross-sectional shape undetermined, the effect of certain variations in sc… more
Date: October 1947
Creator: Brown, W. Byron & Bradshaw, Guy R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of Coupled Modes and Frequencies of Swept Wings by Use of Power Series

Description: "A solution is presented for the coupled modes and frequencies of swept wings mounted on a fuselage. The energy method is used in conjunction with power series to obtain the characteristic equations for both symmetrical and asymmetrical vibration. A numerical example which is susceptible to exact solution is presented, and the results for the exact solution and the solution presented in this paper show excellent agreement" (p. 1).
Date: October 20, 1947
Creator: Anderson, Roger A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of Outboard Nacelle for the XB-36 Airplane

Description: From Summary: "An investigation of two 1/14 scale model configurations of an outboard nacelle for the XB-36 airplane was made in the Langley two-dimensional low-turbulence tunnels over a range of airplane lift coefficients (C (sub L) = 0.409 to C(sub L) = 0.943) for three representative flow conditions. The purpose of the investigation was to develop a low-drag wing-nacelle pusher combination which incorporated an internal air-flow system. The present investigation has led to the development of… more
Date: October 31, 1947
Creator: Nuber, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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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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 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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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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Estimation of Range of Stability Derivatives for Current and Future Pilotless Aircraft

Description: Memorandum presenting an analysis made of the probable range of the stability parameters of present and future missiles. Included is a short review of the dynamic theory and some of the factors and assumptions influencing the stability derivatives and equations of motion.
Date: October 8, 1947
Creator: Pitkin, Marvin & Ankenbruck, Herman O.
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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Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Lateral- and Directional-Stability and Control Characteristics

Description: "This report contains the flight-test results of the lateral and directional-stability and control phase (including tests with wing-tip tanks) of a general flying-qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). These tests were conducted at indicated airspeeds up to 494 miles per hour (0.691 Mach number) at low altitude and up to 378 miles per hour (0.816 Mach number) at high altitude. These tests showed that the flying qualities of the airplane were for the most par… more
Date: October 24, 1947
Creator: Anderson, Seth B. & Cooper, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Tests of a 1/16-Scale Model of the Chance Vought XF5U-1 Airplane, TED No. NACA 2349

Description: "Spin tests of a 1/16-scale model of the Chance Vought XF5U-1 airplane have been performed in the Langley 20-foot free-spinning tunnel. The effect of control position and movement upon the erect and inverted spin and recovery characteristics as well as the effects of propellers, of stability flaps, and of various revisions to the design configuration have been determined for the normal fighter loading. The investigation also included spin recovery parachute, tumbling, and pilot-escape tests" (p… more
Date: October 17, 1947
Creator: White, Richard P.
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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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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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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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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Investigation of High-Lift and Stall-Control Devices on a NACA 64-Series 42 Degree Sweptback Wing With and Without Fuselage

Description: Report presenting an investigation of a 42 degree sweptback wing of aspect ratio 4, taper ratio 0.625, and NACA 64-series airfoil sections to study several proposed devices for increasing the maximum lift coefficient and improving the longitudinal stability characteristics of sweptback wings at the stall. Some of the devices tested included leading-edge flaps and slats, trailing-edge split and extended split flaps, upper-surface split flaps, and upper-surface fences. The results regarding the c… more
Date: October 14, 1947
Creator: Graham, Robert R. & Conner, D. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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