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

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Investigation of Pressure Losses in Several Turbosupercharger Nozzle Hoses

Description: Memorandum presenting surveys of the impact pressure of the flow to obtain information for determining pressure losses in four different turbosupercharger nozzle boxes. The data indicated substantial differences in total head loss among the boxes and the existence of sharply defined high-loss regions in portions of the nozzle annulus.
Date: February 11, 1947
Creator: Lord, Albert M. & Donnola, Joseph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The interdependence of various types of autoignition and knock

Description: A study of the relations existing among pin-point autoignition, homogeneous autoignition, and knock has been made by means of the NACA high-speed camera and the full-view combustion apparatus. High-speed photographic records of combustion, together with corresponding pressure-time traces, of benzene, 2,2,3-trimethylbutane, S-4, and M-4 fuels at various engine conditions have shown the engine conditions under which each of these phenomena occur and the relation of these phenomena to one another.
Date: February 10, 1947
Creator: Olsen, H. Lowell & Miller, Cearcy D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Wind-Tunnel Tests of a Model of the Lockheed YP-80A Airplane Including Correlation with Flight Tests and Tests of Dive-Recovery Flaps

Description: "This report contains the results of tests of a 1/3-scale model of the Lockheed YP-90A "Shooting Star" airplane and a comparison of drag, maximum lift coefficient, and elevator angle required for level flight as measured in the wind tunnel and in flight. Included in the report are the general aerodynamic characteristics of the model and of two types of dive-recovery flaps, one at several positions along the chord on the lower surface of the wing and the other on the lower surface of the fuselag… more
Date: February 14, 1947
Creator: Cleary, Joseph W. & Gray, Lyle J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank Tests of a 1/7-Size Dynamic Model of the Grumman XJR2F-1 Amphibian to Determine the Effect of Slotted- and Split-Type Flaps on Take-Off Stability - NACA Model 212, TED No. NACA 2378

Description: From Summary: "Additional tests of a 1/7-size model of the Grumman XJR2F-1 amphibian were made in Langley tank no. 1 to compare the behavior during take-off of the model equipped with split- and slotted-type flaps. The slotted flag had a large effect on locating the forward center-of-gravity limits for stable take-offs. Stable take-offs within the normal operating range of positions of the center of gravity could be made with the split flaps deflected 45 degrees or with the slotted flaps deflec… more
Date: February 6, 1947
Creator: Land, Norman S. & Zeck, Howard
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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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
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Gas-Dynamic Investigations of the Pulse-Jet Tube, Parts 1 and 2

Description: Based upon a simplified representation of the mode of operation of the pulse-jet tube, the effect of the influences mentioned in the title were investigated and it will be shown that, for a jet tube with a form designed to be aerodynamically favorable, the ability to operate is at least questionable. This investigation will account for the important practical observation made by Paul Schmidt that the ratio of the effective valve cross-sectional area to the tube cross section may not be of any r… more
Date: February 1947
Creator: Schultz-Grunow, F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Load Distribution of the Wing of a 3/16-Scale Model of the Douglas XSB2D-1 Airplane with Flaps Deflected

Description: "The tests reported herein were made for the purpose of determining the high-speed load distribution on the wing of a 3/16 scale model of the Douglas XSB2D-1 airplane. Comparisons are made between the root bending moment and section torsional moment coefficients as obtained experimentally and derived analytically. The results show good correlation for the bending moment coefficients but considerable disagreement for the torsional moment coefficients, the measured moments being greater than the … more
Date: February 5, 1947
Creator: Barnes, Robert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Knock-Limited Power Outputs from a CFR Engine Using Internal Coolants 3 - Four Alkyl Amines, Three Alkanolamines, Six Amides, and Eight Heterocyclic Compounds

Description: An investigation of the antiknock effectiveness of various additive-water solutions when used as internal coolants has been conducted at the NACA Cleveland laboratory. Nine compounds have been previously run in a CFR engine and the results are presented. In an effort to find a good anti-knock-coolant additive with more desirable physical properties than those of the nine compounds previously investigated, water solutions of four alkyl amines, three alkanolamines, six amides, and eight heterocyc… more
Date: February 3, 1947
Creator: Imming, Harry S. & Bellman, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of the Effects of Sweep on the Characteristics of a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel

Description: "An untwisted wing, which when unswept has an NACA 65-210 section, an aspect ratio of 9.0 and a taper ration of 2.5:1.0, has been tested with no sweep, and 30 deg and 45 deg of sweepback and sweepforward in conjunction with a typical fuselage at Mach numbers from 0.60 to 0.96 at angles of attack generally between -2 deg and 10 deg in the Langley 8-foot high-speed tunnel. Sweep was obtained by rotating the wing semispans about a point in the plane of symmetry. The normal-force, pitching-moment, … more
Date: February 14, 1947
Creator: Whitcomb, Richard T.
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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Investigation of Rim Cracking in Turbine Wheels with Welded Blades

Description: Rim cracking in turbine wheels with welded blades was evaluated. The problem is explained on the basis of the occurrence of plastic flow in the rim during transient starting conditions when thermal compressive stresses resulting from high-temperature gradients exceed the proportional elastic limit of the material.
Date: February 12, 1947
Creator: Millenson, M. B. & Manson, S. 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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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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Theoretical Evaluation of Methods of Cooling the Blades of Gas Turbines

Description: A study was made of heat transfer in turbine blades and the effects on blade temperature of cooling the blade root and tip, changing the dimensions of the blades, raising the cycle temperatures, insulating with ceramics, and cooling by circulation of air or water through hollow blades. The results indicated that cooling of the root of the blade, shortening the blade, and cooling hollow blades internally with air or liquid offer possibilities of substantial increases in permissible gas temperatu… more
Date: February 11, 1947
Creator: Sanders, J. C. & Mendelson, Alexander
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Gas-Dynamic Investigations of the Pulse-Jet Tube, Parts 1 and 2

Description: "Based upon a simplified representation of the mode of operation of the pulse-jet tube, the effect of the influences mentioned in the title were investigated and it will be shown that, for a jet tube with a form designed to be aerodynamically favorable, the ability to operate is at least questionable" (p. 1).
Date: February 1947
Creator: Shultz-Grunow, F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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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Tank Tests of 1/5.5-Scale Forward Dynamic Model of the Columbia XJL-1 Amphibian - Langley Tank Model 208, TED No. NACA 2336

Description: Tests of a powered dynamic model of the Columbia XJL-1 amphibian were made in Langley tank no.1 to determine the hydrodynamic stability and spray characteristics of the basic hull and to investigate the effects of modifications on these characteristics. Modifications to the forebody chime flare, the step, and the afterbody, and an increase in the angle of incidence of the wing were included in the test program. The seaworthiness and spray characteristics were studied from simulated taxi runs in… more
Date: February 17, 1947
Creator: Havens, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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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On Combustion in a Turbulent Flow

Description: "The characteristics introduced by the turbulence in the process of the flame propagation are considered. On the basis of geometrical and dimensional considerations an expression is obtained for the velocity of the flame propagation in a flow of large scale of turbulence" (p. 1).
Date: February 1947
Creator: Shelkin, K. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Oscillating Circular Airfoil on the Basis of Potential Theory

Description: "Proceeding from the thesis by W. Kinner the present report treats the problem of the circular airfoil in uniform airflow executing small oscillations, the amplitudes of which correspond to whole functions of the second degree in x and y. The pressure distribution is secured by means of Prandtl's acceleration potential. It results in a system of linear equations the coefficients of which can be calculated exactly with the aid of exponential functions and Hankel's functions" (p. 1).
Date: February 1947
Creator: Schade, T. & Krienes, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Monoplane as a Lifting Vortex Surface

Description: "In Prandtl's airfoil theory the monoplane was replaced by a single lifting vortex line and yielded fairly practical results. However, the theory remained restricted to the straight wing. Yawed wings and those curved in flight direction could not be computed with this first approximation; for these the chordwise lift distribution must be taken into consideration. For the two-dimensional problem the transition from the lifting line to the lifting surface has been explained by Birnbaum. In the pr… more
Date: February 1947
Creator: Blenk, Hermann
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lateral Stability Characteristics of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Description: "The XF-12 airplane is a high-performance photo-reconnaissance aircraft designed for the Army Air Forces by the Republic Aviation Corporation. An investigation of a 1/8.33 - scale powered model was made in the Langley l9-foot pressure tunnel to obtain information relative to the aerodynamic design of the airplane. The model was tested with and without the original vertical tail. and with two revised tails. For the revised tail no. 1, the span of the original vertical .tail was increased about 1… more
Date: February 27, 1947
Creator: Pepper, Edward & Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Scale Effect and Optimum Relations for Sea Surface Planning

Description: "From the general dimensional and mechanical similarity theory it follows that a condition of steady motion of a given shape\bottom with constant speed on the surface of water is determined by four nondimensional parameters. By considering the various systems of independent parameters which are applied in theory and practice and special tests, there is determined their mutual relations and their suitability as planning characteristics. In studying the scale effect on the basis of the Prnndtl fo… more
Date: February 1947
Creator: Sedov, L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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