National Advisory Committee for Aeronautics (NACA) - 62 Matching Results

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Aerodynamic Characteristics at High Speeds of Full-Scale Propellers Having Different Shank Designs

Description: "Tests of two 10-foot-diameter two-blade propellers which differed only in shank design have been made in the Langley 16-foot high-speed tunnel. The propellers are designated by their blade design numbers, NACA 10-(5)(08)-03, which had aerodynamically efficient airfoil shank sections, and NACA 10-(5)(08)-03R which had thick cylindrical shank sections typical of conventional blades. The propellers mere tested on a 2000-horsepower dynamometer through a range of blade-angles from 20 degrees to 55 … more
Date: February 13, 1947
Creator: Maynard, Julian D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical Comparison of a Standard Turbojet Engine, a Turbojet Engine with a Tail-Pipe Burner, and a Ram-Jet Engine

Description: From Introduction: "Experimental investigations (reference 1) have shown that in some cases the thrust can be more than doubled by means of tail-pipe burning. A comparison is made of a standard turbojet engine, whose thrust is augmented by tail-pipe burning, and a ram-jet engine. The performance characteristics for the ram-jet engine were computed entirely from theoretical considerations and on the assumption that the burner-inlet velocity was constant."
Date: February 10, 1947
Creator: Krebs, Richard P. & Palasics, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analytical Investigation of the Heat Losses from a U.S. Navy K-Type Airship

Description: From Summary: "The heat losses from the envelope surface of a U.S. Navy K-type airship are evaluated to determine if the use of heat is a feasible means of preventing ice and snow accumulations on lighter-than-air craft during flight and when moored uncovered. Consideration is given to heat losses in clear air (no liquid water present in the atmosphere) and in probable conditions of icing and snow. The results of the analysis indicate that the amount of heat required in flight to raise the surf… more
Date: February 17, 1947
Creator: Hillendahl, Wesley H. & George, Ralph E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of the Analogy Between Water Flow With a Free Surface and Two-Dimensional Compressible Gas Flow

Description: From Introduction: "The development of the measuring apparatus and techniques is presented herein. The application of the analogy to flows through nozzles and about circular cylinders at subsonic velocities extending into supercritical range is also presented."
Date: February 1947
Creator: Orlin, W. James; Lindner, Norman J. & Bitterly, Jack G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bearing strength of some sand-cast magnesium alloys

Description: Report presenting testing to determine the bearing strength characteristics of some magnesium-alloy sand castings and the relation between those and more commonly determined tensile properties. The primary sand-cast magnesium alloys of interest for aircraft design are AM403, AM260, and AM265. Results of all of the tension, compression, and shear tests are provided in tables.
Date: February 1947
Creator: Moore, R. L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculations of the Supersonic Wave Drag of Nonlifting Wings with Arbitrary Sweepback and Aspect Ratio: Wings Swept Behind the Mach Lines

Description: "On the basis of a recently developed theory for finite sweptback wings at supersonic speeds, calculations of the supersonic wave drag at zero lift were made for a series of wings having thin symmetrical biconvex sections with untapered plan forms and various angles of sweepback and aspect ratios. The results are presented in a unified form so that a single chart permits the direct determination of the wave drag for this family of airfoils for an extensive range of aspect ratio and sweepback an… more
Date: February 21, 1947
Creator: Harmon, Sidney M. & Swanson, Margaret D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts Showing Relations Among Primary Aerodynamic Variables for Helicopter-Performance Estimation

Description: "In order to facilitate solutions of the general problem of helicopter selection, the aerodynamic performance of rotors is presented in the form of charts showing relations between primary design and performance variables. By the use of conventional helicopter theory, certain variables are plotted and other variables are considered fixed. Charts constructed in such a manner show typical results, trends, and limits of helicopter performance" (p. 1).
Date: February 1947
Creator: Talkin, Herbert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Comparison of the Lateral Motion Calculated for Tailless and Conventional Airplanes

Description: Theoretical analysts of lateral dynamic motion of tailless and conventional airplanes was made for fighter and heavy transport. Their reactions to a lateral gust and control power required by each for simple maneuvers were determined and compared. Both types of airplanes require almost identical aileron control power to perform a given maneuver; tailless airplane requires about 1-2 to 1-3 directional control power of conventional airplane. Tailless airplane also shows greatest displacement for … more
Date: February 1947
Creator: Harper, Charles W. & Jones, Arthur L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Wind-Tunnel Predictions with Flight Measurements of the Longitudinal-Stability and -Control Characteristics of a Douglas BTD-1 Airplane

Description: "Low Mach number longitudinal-stability and control characteristics as predicted by use of wind tunnel data from a powered 3/16-scale model are compared with flight test measurements of a Navy BTD-1 airplane. The accuracy of the wind tunnel data and the discrepancies involved in attempting to correlate with flight data are discussed and analyzed. The comparison showed that wind tunnel predictions were, in general, in good agreement with flight test data" (p. 1).
Date: February 13, 1947
Creator: Bunnell, Mort V. & Delany, Noel K.
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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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, 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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Cyclic Engine Test of Cast Vitallium Turbine Buckets - I

Description: "An investigation was conducted to correlate the engine service performance of cast Vitallium turbine buckets with standard laboratory metallurgical data. Data were obtained from four I-40 turbine wheels of Timken alloy with cast Vitallium buckets. In order to accelerate bucket deterioration, the turbine wheels were subjected to 20-minute cycles consisting of 5 minutes at idle and 15 minutes at rated speed" (p. 1).
Date: February 7, 1947
Creator: Farmer, J. Elmo; Darmara, F. N. & Poulson, Francis D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Development of Inboard Nacelle for the XB-36 Airplane

Description: From Summary: "A series of investigations of several 1/14-scale models of an inboard nacelle for the XB-36 airplane was made in the Langley two-dimensional low-turbulence tunnels. The purpose of these investigations was to develop a low-drag wing-nacelle pusher combination which incorporated an internal air-flow system. As a result of these investigations, a nacelle was developed which had external drag coefficients considerably lower than the original basic form with the external nacelle drag … more
Date: February 11, 1947
Creator: Nuber, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Device for Measuring Principal Curvature and Principal Strains on a Nearly Plane Surface

Description: Note presenting a device which makes possible the measurement of principal extreme fiber bending strains over a circular area with a radius of 0.94 inch with a systematic error on 0.1-inch sheet of the order of 0.00003. Equations are presented for computing median fiber strains from the measured curvatures and strains at the surface and from the thickness of the sheet.
Date: February 1947
Creator: McPherson, A. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having aspect ratios of 1.5 and 2.7 as determined by flight tests at supersonic speeds

Description: Report presenting tests to determine the effects of sweepback angle and aspect ratio on the drag of an NACA 65-009 airfoil at supersonic speeds. The results indicated that for the range of Mach numbers investigated, increasing the sweepback angle and decreasing the aspect ratio reduced the value of the wing drag coefficient.
Date: February 24, 1947
Creator: Alexander, Sidney R. & Katz, Ellis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Measurements of a 34 Degree Swept-Forward and Swept-Back NACA 65-009 Airfoil of Aspect Ratio 2.7 as Determined by Flight Tests at Supersonic Speeds

Description: Report presenting the results of flight testing to determine the zero-lift drag of an NACA 65-009 airfoil at a specified aspect ratio. The results are compared to previous testing of unswept and swept-back arrangements. The swept-forward and swept-back airfoils were found to produce lower values of zero-drag lift than the unswept airfoil.
Date: February 20, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Centrifugal Force on the Elastic Curve of a Vibrating Cantilever Beam

Description: Report presenting the results of a study to determine the effect of rotation on the dynamic-stress distribution in vibrating cantilever beams. Both theoretical and experimental results are obtained by means of stroboscopic photographs and strain gauges. Both types of results indicated that the introduction of centrifugal force had no effect on the maximum dynamic-stress locations in a vibrating cantilever beam fixed at the center of rotation within the investigated speed range.
Date: February 1947
Creator: Simpkinson, Scott H.; Eatherton, Laurel J. & Millenson, Morton B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of high solidity on propeller characteristics at high forward speeds from wind-tunnel tests of the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 two-blade propellers

Description: From Summary: "Tests of two-blade propellers having the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 blade designs (blade activity factors of 179 and 263, respectively) have been made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 70 degrees for free-stream Mach numbers from 0.165 to 0.725 to determine the effects of high solidity and compressibility on propeller characteristics. The tests are part of a general investigation of propellers at high forwar… more
Date: February 27, 1947
Creator: Delano, James B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects on Performance of Changing the Division of Work Between Increase of Angular Velocity and Increase of Radius of Rotation in an Impeller

Description: Note presenting the effect on the performance of increasing the angular velocity of an impeller and consequently increasing the amount of work of compression resulting from the angular acceleration of the air in the impeller for four impellers in combination with a vaneless diffuser in a variable-component supercharger test rig of a range of tip speeds. Results regarding a comparison of performance, analysis of volume-flow limitations, and use of blade-inlet relative Mach number as a design par… more
Date: February 1947
Creator: Ginsburg, Ambrose; Ritter, William K. & Palasics, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exhaust-valve temperatures in a liquid-cooled aircraft-engine cylinder as affected by engine operating variables

Description: Report presenting an investigation of the operating temperatures of sodium-cooled exhaust valves in a liquid-cooled cylinder for a large variety of engine conditions by means of a thermocouple embedded in the valve head. The engine operating variables that affected the valve temperature most for a given percentage change in the operating variable included fuel-air ratio, indicated mean effective pressure, compression ratio, and spark advance. Results regarding temperature variations in constant… more
Date: February 1947
Creator: Sutor, Alois T.; Corrington, Lester C. & Dudugjian, Carl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation

Description: Flight and ground investigations have been made to compare an exhaust-ejector installation with a standard exhaust-collector-ring installation on air-cooled aircraft engines in a twin-engine airplane. The ground investigation allowed that, whereas the standard engine would have overheated above 600 horsepower, the engine with exhaust ejectors cooled at take-off operating conditions at zero ram. The exhaust ejectors provided as much cooling with cowl flaps closed as the conventional cowl flaps i… more
Date: February 14, 1947
Creator: Acker, Loren W. & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of Internal Cockpit Pressures in Several Fighter-Type Airplanes

Description: Report presenting flight measurements of internal cockpit pressure in several fighter-type airplanes equipped with conventional or bubble canopies. Data are presented for variation in cockpit pressure with indicated airspeed and angle of sideslip for canopy-closed and canopy-open positions. A method is also included for predicting cockpit pressure in accelerated flight from measurements made in accelerated flight.
Date: February 1947
Creator: Danforth, Edward C. B., III & Reeder, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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