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An Analysis of the Full-Floating Journal Bearing

Description: Report discussing an analysis of the operating characteristics of a full-floating journal bearing, a bearing in which a floating sleeve is located between the journal and bearing surfaces, is presented together with charts from which the performance of such bearings may be predicted.
Date: January 1, 1947
Creator: Shaw, M. C. & Nussdorfer, T. J., Jr.
Partner: UNT Libraries Government Documents Department
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Charts for determining the characteristics of sharp-nose airfoils in two-dimensional flow at supersonic speeds

Description: Solutions of the Hugoniot shock equations and Meyer expansion equations are plotted in such a manner as to permit the pressure distribution, the local Mach number, and the angles of shock waves on arbitrary sharp-nose airfoils at supersonic speeds to be obtained directly. (author).
Date: January 1947
Creator: Ivey, H. Reese; Stickle, George W. & Schuettler, Alberta
Partner: UNT Libraries Government Documents Department
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Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 0-1HTA Magnesium Alloy

Description: Column and plate compressive strengths of extruded 0-1HTA magnesium alloy were determined both within and beyond the elastic range from tests of flat end H-section columns and from local instability tests of H-, Z-, and channel section columns. These tests are part of an extensive research investigation to provide data on the structural strength of various aircraft materials. The results are presented in the form of curves and charts that are suitable for use in the design and analysis of aircr… more
Date: January 1947
Creator: Heimerl, George J. & Niles, Donald E.
Partner: UNT Libraries Government Documents Department
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Compressible Flow Tables for Air

Description: "This paper contains a tabulation of functions of the Mach number which are frequently used in high-speed aerodynamics. The tables extend from M = 0 to M = 10.0 in increments of 0.01 and are based on the assumption that air is a perfect gas having a specific heat ratio of 1.400" (p. 1).
Date: 1947
Creator: Burcher, Marie A.
Partner: UNT Libraries Government Documents Department
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Determination of elastic stresses in gas-turbine disks

Description: A method is presented for the calculation of elastic stresses in symmetrical disks typical of those of a high-temperature gas turbine. The method is essentially a finite-difference solution of the equilibrium and compatibility equations for elastic stresses in a symmetrical disk. Account can be taken of point-to-point variations in disk thickness, in temperature, in elastic modulus, in coefficient of thermal expansion, in material density, and in Poisson's ratio. No numerical integration or tri… more
Date: 1947
Creator: Manson, S. S.
Partner: UNT Libraries Government Documents Department
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Effect of brake forming in various tempers on the strength of Alclad 75S-T aluminum-alloy sheet

Description: Results are presented of tests to determine the effect of brake forming in various tempers on the strength of Alclad 75S-T aluminum alloy sheet in the direction parallel to the brake. The tensile and compressive strengths of Alclad 75S-T sheet, formed in the O and W tempers, were either increased or little affected compared with those of similarly treated unformed material. When Alclad 75S-T sheet 'as received' was formed, however, the tensile yield stress was reduced about 7 percent for the wi… more
Date: January 1947
Creator: Woods, Walter & Heimerl, George J.
Partner: UNT Libraries Government Documents Department
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Effect of rivet or bolt holes on the ultimate strength developed by 24S-T and Alclad 75S-T sheet in incomplete diagonal tension

Description: From Summary: "Strength tests were made of a number of 24S-T and Alclad 75S-T aluminum alloy shear webs to determine the effect of rivet or bolt holes on the shear strength. Data were obtained for webs which approached a condition of pure shear stress as well as for webs with well-developed diagonal tension. The rivet factor (pitch minus diameter), divided by pitch, was varied from approximately 0.81 to 0.62. These tests indicated that the shear stresses on the gross section were nearly constan… more
Date: January 1947
Creator: Levin, L. Ross & Nelson, David H.
Partner: UNT Libraries Government Documents Department
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Effect of Various Methods of Boundary-Layer Control on Performance of V-1710-93 Engine-Stage Supercharger

Description: "Four methods of boundary-layer control were tried during an investigation to improve the flow in the impeller passages of a V-1710-93 engine-stage supercharger. The boundary layer along the impeller front shroud was removed by suction. In one method the removal was accomplished by recirculation of the air to the impeller inlet; in another method, by external removal. In the other methods, slots were cut through the impeller-blade faces first at 30 percent and then at 30 and 70 percent of the m… more
Date: January 1947
Creator: Kohl, Robert C. & Diggs, Donald R.
Partner: UNT Libraries Government Documents Department
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Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms: September 5, 1946 to September 10, 1946 at Orlando, Florida

Description: Tables I and II of this report summarize the gust and draft velocity data for thunderstorm flights 31, 32, and 33 of September 5, 1946, September 6, 1946, and September 10, 1946, respectively. These data were evaluated from records of NACA instruments installed in P-61C airplanes and are of the type presented for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient air temperature during thunderstorm surveys… more
Date: 1947
Creator: Tolefson, H. B.
Partner: UNT Libraries Government Documents Department
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Flight Investigation on a Fighter-Type Airplane of Factors Which Affect the Loads and Load Distributions on the Vertical Tail Surfaces During Rudder Kicks and Fishtails

Description: "Results are presented of a flight investigation conducted on a fighter-type airplane to determine the factors which affect the loads and load distributions on the vertical tail surfaces in maneuvers. An analysis is made of the data obtained in steady flight, rudder kicks, and fishtail maneuvers. For the rudder kicks, the significant loads were the "deflection load" resulting from an abrupt control deflection and the "dynamic load" consisting of a load corresponding to the new static equilibriu… more
Date: 1947
Creator: Boshar, John
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Tests of a 1/27-Scale Model of the Douglas XF3D-1 Airplane, TED No. NACA DE 312

Description: "Free-spinning-tunnel tests have been made on a 1/27-scale model of the Douglas XF3D-1 airplane to confirm a preliminary evaluation made of the airplane spin and recovery characteristics and previously reported. Recovery characteristics were satisfactory for erect and inverted spins when the model was in the clean condition. When the slow-down brakes were open, recoveries were slow. The pedal force necessary to reverse the airplane rudder during a spin will be within the physical capabilities o… more
Date: 1947
Creator: Scher, Stanley H.
Partner: UNT Libraries Government Documents Department
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Frequency-Response Method for Determination of Dynamic Stability Characteristics of Airplanes With Automatic Controls

Description: "A frequency-response method for determining the critical control-gearing and hunting oscillations of airplanes with automatic pilots is presented. The method is graphical and has several advantages over the standard numerical procedure based on Routh's discriminant. The chief advantage of the method is that direct use can be made of the measured response characteristics of the automatic pilot. This feature is especially useful in determining the existence, amplitude, and frequency of the hunti… more
Date: 1947
Creator: Greenberg, Harry
Partner: UNT Libraries Government Documents Department
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Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed

Description: The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
Date: January 1947
Creator: Ackeret, J.; Feldmann, F. & Rott, N.
Partner: UNT Libraries Government Documents Department
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Isolated and Cascade Airfoils With Prescribed Velocity Distribution

Description: "An exact solution of the problem of designing an airfoil with a prescribed velocity distribution on the suction surface in a given uniform flow of an incompressible perfect fluid is obtained by replacing the boundary of the airfoil by vortices. By this device, a method of solution is developed that is applicable both to isolated airfoils and to airfoils in cascade. The conformal transformation of the designed airfoil into a circle can then be obtained and the velocity distribution at any angle… more
Date: 1947
Creator: Goldstein, Arthur W. & Jerison, Meyer
Partner: UNT Libraries Government Documents Department
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Lateral-control characteristics of various spoiler arrangements as measured in flight

Description: Report presenting an investigation of the lateral-control characteristics of several spoiler arrangements located near the wing trailing edge in flight. In all cases, the control response was satisfactory and the variation of rolling effectiveness with control deflections was smooth and nearly linear. Results regarding response characteristics, rolling effectiveness, control-force and hinge-moment characteristics, yawing characteristics, effects of altitude, characteristics near the stall, and … more
Date: January 1947
Creator: Spahr, J. Richard
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Stalling Characteristics of a 1/8.33-Scale Model of the Republic XF-12 Airplane

Description: "The XF-12 airplane is a high performance, photo-reconnaissance aircraft designed by the Republic Aviation Corporation for Army Air Forces. A series of tests of a 1/8.33-scale powered model was conducted in the Langley 9-foot pressure tunnel to obtain information relative to the aerodynamic design of the airplane. This report presents the results of tests to determine the static longitudinal stability and stalling characteristics of the model" (p. 1).
Date: 1947
Creator: Pepper, Edward & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department
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Method of Characteristics for Three-Dimensional Axially Symmetrical Supersonic Flows

Description: "An approximation method for three-dimensional axially symmetrical supersonic flows is developed; it is based on the characteristics theory (represented partly graphically, partly analytically). Thereafter this method is applied to the construction of rotationally symmetrical nozzles" (p. 1).
Date: January 1947
Creator: Sauer, R.
Partner: UNT Libraries Government Documents Department
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Notes on the theoretical characteristics of two-dimensional supersonic airfoils

Description: The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic characteristics of two-dimensional supersonic airfoils. A discussion is given of the effect of thickness ratio, free-stream Mach number, angle of attack, camber, thickness distribution, and aileron deflection. The calculations indicated that the minimum drag of supersonic airfoils is obtained when the maximum thickness is behind the 0.50 chord. The center of pressure obtained for a symmetrical sup… more
Date: January 1947
Creator: Ivey, H. Reese
Partner: UNT Libraries Government Documents Department
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Possibilities of Reducing the Length of Axial Superchargers for Aircraft Motors

Description: Axial blowers are gaining importance as aircraft engine superchargers. However, the pressure head obtainable per stage is small. Due to the necessary great number of stages, the physical length of the blower becomes too great for an airworthy device. This report discusses several types of construction that permit a reduction in the length of the blower.
Date: January 1947
Creator: Eckert, B.
Partner: UNT Libraries Government Documents Department
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Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine. 5 - Performance of Modified Engine

Description: From Summary: "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance characteristics of a modified X24C-4B turbojet engine over a range of simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.25 to 1.07, and engine speeds from 4000 to 12,500 rpm. The engine was modified by the manufacturer to improve the velocity and temperature profiles within the engine. Performance data are graphically presented to show the ef… more
Date: 1947
Creator: Prince, William R. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department
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Pressure-Distribution Measurements on a Straight and on a 35 Degree Swept-Back Tapered Wing

Description: "The spanwise lift-distribution measurements in straight air flow on a straight and a 35 deg swept-back tapered wing (NACA airfoil section 0012) are compared with theory for two angles of attack each (alpha approx. 6 deg and alpha approx. 12 deg) in the unstalled range of flow. The complete pressure distribution for the greater of the two angles is indicated" (p. 1).
Date: January 1947
Creator: Thiel, A. & Weissinger, J.
Partner: UNT Libraries Government Documents Department
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Pressure Distributions and Force Tests of an NACA 65-210 Airfoil Section With a 50-Percent-Chord Flap

Description: Note presenting pressure distributions and force measurements in the two-dimensional low-turbulence pressure tunnel at low Mach numbers and high Reynolds numbers of an NACA 65-210 airfoil equipped with a 50-percent-chord plain flap. Tests were carried out for flap deflections of 0, 4, 7, and 10 degrees. These flap deflections provided considerably reduced drag coefficients at life coefficients above the design range of the plain airfoil.
Date: January 1947
Creator: Klein, Milton M.
Partner: UNT Libraries Government Documents Department
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Simulated Altitude Investigation of Stewart-Warner Model 906-B Combustion Heater

Description: "An investigation has been conducted to determine thermal and pressure-drop performance and the operational characteristics of a Stewart-Warner model 906-B combustion heater. The performance tests covered a range of ventilating-air flows from 500 to 3185 pounds per hour, combustion-air pressure drops from 5 to 35 inches of water, and pressure altitudes from sea level to 41,000 feet. The operational characteristics investigated were the combustion-air flows for sustained combustion and for consi… more
Date: January 1947
Creator: Ebersbach, Frederick R. & Cervenka, Adolph J.
Partner: UNT Libraries Government Documents Department
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Spark-Timing Control Based on Correlation of Maximum-Economy Spark Timing, Flame-Front Travel, and Cylinder-Pressure Rise

Description: "An investigation was conducted on a full-scale air-cooled cylinder in order to establish an effective means of maintaining maximum-economy spark timing with varying engine operating conditions. Variable fuel-air-ratio runs were conducted in which relations were determined between the spark travel, and cylinder-pressure rise. An instrument for controlling spark timing was developed that automatically maintained maximum-economy spark timing with varying engine operating conditions" (p. 1).
Date: 1947
Creator: Cook, Harvey A.; Heinicke, Orville H. & Haynie, William H.
Partner: UNT Libraries Government Documents Department
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