National Advisory Committee for Aeronautics (NACA) - 743 Matching Results

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Comparisons of Theoretical and Experimental Lift and Pressure Distributions on Airfoils in Cascade

Description: Note presenting comparisons of theoretical and experimental airfoil lift coefficients and pressure distributions made for two cascades of entrance vanes and three cascades of blower blades with NACA 6-series airfoils, and for one cascade of turbine blades. Results regarding the entrance vanes, blower blades, turbine blades, and possibilities of three-dimensional effects are provided.
Date: July 1947
Creator: Katzoff, S.; Bogdonoff, Harriet E. & Boyet, Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compilation of Test Data on 111 Free-Spinning Airplane Models Tested in the Langley 15-Foot and 20-Foot Free-Spinning Tunnels

Description: "A compilation of free-spinning-airplane model data on the spin and recovery characteristics of 111 airplanes is presented. These data were previously published in separate memorandum reports and were obtained from free-spinning tests in the Langley 15-foot and the Langley 20-foot free-spinning tunnels. The model test data presented include the steady-spin and recovery characteristics of each model for various combinations of aileron and elevator deflections and for various loadings and dimensi… more
Date: May 15, 1947
Creator: Malvestuto, Frank S., Jr.; Gale, Lawrence J. & Wood, John H.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compression Shocks of Detached Flow

Description: "It is known that compression shocks which lead from supersonic to subsonic velocity cause the flow to separate on impact on a rigid wall. Such shocks appear at bodies with circular symmetry or wing profiles on locally exceeding sonic velocity, and in Laval nozzles with too high a back pressure. The form of the compression shocks observed therein is investigated" (p. 1).
Date: June 1947
Creator: Eggink
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compressive-Strength Comparisons of Panels Having Aluminum-Alloy Sheet and Stiffeners With Panels Having Magnesium-Alloy Sheet and Aluminum Alloy Stiffeners

Description: Report presenting comparisons of 24S-T aluminum-alloy flat compression panels with longitudinal Z-section stiffeners and panels with flat FS-1E magnesium-alloy sheet and longitudinal 24S-T aluminum-alloy Z-section stiffeners. The use of the composite magnesium-alloy, aluminum-alloy construction permits wider stiffener spacing with little to not loss in structural efficiency or stress for local buckling. Results regarding stiffener spacing, proportions, and consideration of the different materia… more
Date: April 1947
Creator: Dow, Norris F.; Hickman, William A. & McCracken, Howard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compressive strength of 24S-T aluminum-alloy flat panels with longitudinal formed hat-section stiffeners having a ratio of stiffener thickness to skin thickness equal to 1.00

Description: Report presenting results for a part of a test program on 24S-T aluminum-alloy flat compression panels with longitudinal formed hat-section stiffeners. This particular part of the program is concerned with panels in which the thickness of the stiffener material is equal to the thickness of the skin. Results regarding the hat-stiffened panels and a comparison of hat-stiffened and Z-stiffened panels are provided.
Date: September 1947
Creator: Hickman, William A. & Dow, Norris F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Computed Performance of a Composite Engine Based on Experimental Data for a Single-Cylinder Conventional Aircraft Engine Converted to Compression-Ignition Operation

Description: Memorandum presenting a determination of the performance of a single-cylinder spark-ignition engine modified to operate on a compression-ignition cycle with a compression ratio of 8.0. Experimental data were obtained at an inlet-manifold pressure of 100 inches of mercury absolute, fuel-air ratios of 0.040 and 0.025, and engine exhaust pressures of 30 to 100 inches of mercury absolute. Results regarding single-cylinder-engine experimental data and full-scale-engine calculations are provided.
Date: February 3, 1947
Creator: McCoy, J. Arnold & Szel, Frank
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Computed Temperature Distribution and Cooling of Solid Gas-Turbine Blades

Description: "Computations were made to determine the temperature distribution and cooling of solid gas-turbine blades.A range of temperatures was used from 1500 degrees to 2500 degrees F, blade-root temperatures from 100 degrees to 1000 degrees F, blade thermal conductivity from 8 to 220 BTU/(hr)(sq ft)(degrees F/ft), and net gas to metal heat transfer coefficients from 75 to 250 BTU/(hr)(sq ft)(degrees F)" (p. 1).
Date: February 11, 1947
Creator: Reuter, J. George & Gazley, Carl, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Concerning the Velocity of Evaporation of Small Droplets in a Gas Atmosphere

Description: "The evaporation velocity of liquid droplets under various conditions is theoretically calculated and a number of factors are investigated which are neglected in carrying out the fundamental equation of Maxwell. It is shown that the effect of these factors at the small drop sizes and the small weight concentrations ordinarily occurring in fog can be calculated by simple corrections. The evaporation process can be regarded as quasi-stationary in most cases" (p. 1).
Date: August 1947
Creator: Fuchs, N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cones in Supersonic Flow

Description: "In the case of cones in axially symmetric flow of supersonic velocity, adiabatic compression takes place between shock wave and surface of the cone. Interpolation curves betwen shock polars and the surface are therefore necessary for the complete understanding of this type of flow. They are given in the present report by graphical-numerical integration of the differential equation for all cone angles and airspeeds" (p. 1).
Date: August 1947
Creator: Hantzsche, W. & Wendt, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Considerations of the Total Drag of Supersonic Airfoil Sections

Description: The results of calculations of the viscous and pressure drags of some two-dimensional supersonic airfoils at zero lift are presented. The results indicate that inclusion of viscous drag alters many previous results regarding the desirability of certain airfoil shapes for securing low drags at supersonic speeds. At certain Reynolds and Mach numbers, for instance, a circular-arc airfoil may theoretically have less drag than the previously advocated symmetrical wedge-shape profile; although under … more
Date: July 1947
Creator: Ivey, H. Reese & Klunker, E. Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling Characteristics of the V-1650-7 Engine, 1, Coolant-Flow Distribution, Cylinder Temperatures, and Heat Rejections at Typical Operating Conditions

Description: From Summary: "An investigation was conducted to determine the coolant-flow distribution, the cylinder temperatures, and the heat rejections of the V-1650-7 engine . The tests were run a t several power levels varying from minimum fuel consumption to war emergency power and at each power level the coolant flows corresponded to the extremes of those likely to be encountered in typical airplane installations, A mixture of 30-percent ethylene glycol and 70-percent water was used as the coolant. T… more
Date: May 23, 1947
Creator: Povolny, John H. & Bogdan, Louis J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling Characteristics of the V-1650-7 Engine 2 - Effect of Coolant Conditions on Cylinder Temperatures and Heat Rejection at Several Engine Powers

Description: From Summary: "An investigation has been conducted on a V-1650-7 engine to determine the cylinder temperatures and the coolant and oil heat rejections over a range of coolant flows (50 to 200 gal/min) and oil inlet temperatures (160 to 2150 F) for two values of coolant outlet temperature (250 deg and 275 F) at each of four power conditions ranging from approximately 1100 to 2000 brake horsepower. Data were obtained for several values of block-outlet pressure at each of the two coolant outlet te… more
Date: September 24, 1947
Creator: Povolny, John H.; Bogdan, Louis J. & Chelko, Louis J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines 1 - Effects of Addition of Fins to Blade Tips and Rotor, Admission of Cooling Air Through Part of Nozzles, and Change in Thermal Conductivity of Turbine Components

Description: "An analysis was developed for calculating the radial temperature distribution in a gas turbine with only the temperatures of the gas and the cooling air and the surface heat-transfer coefficient known. This analysis was applied to determine the temperatures of a complete wheel of a conventional single-stage impulse exhaust-gas turbine. The temperatures were first calculated for the case of the turbine operating at design conditions of speed, gas flow, etc. and with only the customary cooling a… more
Date: February 11, 1947
Creator: Brown, W. Byron
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades

Description: An analysis is presented of rim cooling of gas-turbine blades; that is, reducing the temperature at the base of the blade (wheel rim), which cools the blade by conduction alone. Formulas for temperature and stress distributions along the blade are derived and, by the use of experimental stress-rupture data for a typical blade alloy, a relation is established between blade life (time for rupture), operating speed, and amount of rim cooling for several gas temperatures. The effect of blade parame… more
Date: March 18, 1947
Creator: Wolfenstein, Lincoln; Meyer, Gene L. & McCarthy, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines, 3, Analysis of Rotor and Blade Temperatures in Liquid-Cooled Gas Turbines

Description: A theoretical analysis of the radial temperature distribution through the rotor and constant cross sectional area blades near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the rotor and blade temperatures of a specific turbine using a gas flow of 55 pounds per second, a coolant flow of 6.42 pounds per second, and an average coolant temperature of 200 degrees F. The effect of using kerosene, water, and ethylene glycol was determined. The effect … more
Date: February 11, 1947
Creator: Brown, W. Byron & Livingood, John N. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines, 4 - Calculated Temperature Distribution in the Trailing Part of a Turbine Blade Using Direct Liquid Cooling

Description: A theoretical analysis of the temperature distribution through the trailing portion of a blade near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the hot spot temperatures at the trailing edge and influence of design variables. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
Date: April 18, 1947
Creator: Brown, W. Byron & Monroe, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines 6 - Computed Temperature Distribution Through Cross Section of Water-Cooled Turbine Blade

Description: "A theoretical analysis of the cross-sectional temperature distribution of a water-cooled turbine blade was made using the relaxation method to solve the differential equation derived from the analysis. The analysis was applied to specific turbine blade and the studies icluded investigations of the accuracy of simple methods to determine the temperature distribution along the mean line of the rear part of the blade, of the possible effect of varying the perimetric distribution of the hot gas-to… more
Date: May 1, 1947
Creator: Livingood, John N. B. & Sams, Eldon W.
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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Correlation of Experimental and Calculated Effects of Product of Inertia on Lateral Stability

Description: Report presenting a correlation of the experimental and calculated effects of the product of inertia on the stability of lateral oscillations of airplanes. The experimental and calculated boundaries were in good agreement with one another, but neglecting the product of inertia led to wide discrepancies. Results regarding stability and its influence on general flight behavior are provided.
Date: July 1947
Creator: McKinney, Marion O., Jr. & Drake, Hubert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation of the Trim Limits of Stability Obtained for a PB2Y-3 Flying Boat and a 1/8-Size Powered Dynamic Model

Description: Tests of a PB2Y-3 flying boat were made at the U.S. Naval Air Station, Patuxent River, Md., to determine its hydrodynamic trim limits of stability. Corresponding tests were also made of a 1/8-size powered dynamic model of the same flying boat in Langley tank no. 1. During the tank tests, the full-size testing procedure was reproduced as closely as possible in order to obtain data for a direct correlation of the results. As a nominal gross load of 66,000 pounds, the lower trim limits of the full… more
Date: April 22, 1947
Creator: Garrison, Charlie C.; Goldenbaum, David M. & Hacskaylo, Andrew
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation of Two Experimental Methods of Determining the Rolling Characteristics of Unswept Wings

Description: Note presenting the rolling moments of one tapered wing and two geometrically similar wings in rolling flow with the wing stationary and in straight flow with forced rotation of the wing to obtain a correlation between the two methods of testing and to determine the rolling characteristics of the wings. The results showed that for unswept wings the rolling characteristics obtained by rotation of the air agreed with those obtained by forced rotation of the wing.
Date: May 1947
Creator: MacLachlan, Robert & Letko, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical Combinations of Shear and Direct Stress for Simply Supported Rectangular Flat Plates

Description: Note presenting an investigation of the buckling of a simply supported rectangular flat plate under combinations of shear and direct stress by means of an energy method. The critical combinations of stress for several length-width ratios were determined to an accuracy of about 1 percent in conjunction with a modified matrix iteration method. Results regarding the shear and longitudinal stress and shear and transverse stress are provided.
Date: March 1947
Creator: Batdorf, S. B. & Stein, Manuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical Combinations of Shear and Longitudinal Direct Stress for Long Plates With Transverse Curvature

Description: Note presenting a theoretical solution for the buckling stresses of long plates with transverse curvature loaded in shear and longitudinal direct stress. The theoretical critical-stress combinations for plates with either simply supported or clamped edges are given in figures and tables and a comparison is made with previous theoretical solutions. Results regarding the theoretical results, empirical results and design curves, and some interaction formulas are provided.
Date: June 1947
Creator: Batdorf, S. B.; Schildcrout, Murry & Stein, Manuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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