National Advisory Committee for Aeronautics (NACA) - 74 Matching Results

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Appreciation and determination of the hydrodynamic qualities of seaplanes

Description: Report presenting a summary of the hydrodynamic qualities of interest in the normal operation of a seaplane, established over a period of years by model testing and by some knowledge of full-size operation. Results regarding longitudinal stability and control, landing stability, seaworthiness, performances, and lateral stability and control are provided.
Date: May 1947
Creator: Parkinson, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending Stresses Due to Torsion in a Tapered Box Beam

Description: Note presenting a method for the calculation of bending stresses due to torsion in a tapered box beam. A special taper was assumed in which all flanges, if extended, would meet at a point. The results obtained by this method were compared with experimental data obtained from tests performed on a tapered box beam.
Date: May 1947
Creator: Kruszewski, Edwin T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-Induced Upwash for Yawed and Swept-Back Wings in Closed Circular Wind Tunnels

Description: Report presenting a determination of the tunnel-induced velocities for yawed and swept-back airfoils in a closed circular wind tunnel. Calculations were performed for elemental horseshoe vortices with one tip of the bound vortex on the tunnel axis for a range of yaw angles and bound-vortex lengths.
Date: May 1947
Creator: Eisenstadt, Bertram J.
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: Report presenting calculations of the supersonic wave drag at zero lift for a series of wings with thin symmetrical biconvex sections with untapered plan forms and various angles of sweepback and aspect ratios.
Date: May 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 for stress analysis of reinforced circular cylinders under lateral loads

Description: Report presenting charts with coefficients for the stress analysis of a reinforced circular cylinder. They allow for the rapid determination of sheer flows and direct stresses in the sheet of a cylinder as well as the shear forces, axial forces, and bending moments in the rings. Separate charts are also given for three basic ring loadings.
Date: May 1947
Creator: Kempner, Joseph & Duberg, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Collection and analysis of wind-tunnel data on the characteristics of isolated tail surfaces with and without end plates

Description: Report presenting the aerodynamic characteristics of 19 isolated tail surfaces, which have been determined by wind tunnel tests. Testing was also made of rectangular airfoils of various aspect ratios with and without double end plates of various shapes. The analysis indicated that the slope of the lift curve could be predicted within 10 percent for all models by use of lifting-surface-theory equations.
Date: May 1947
Creator: Bates, 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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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 Shear Stress of Curved Rectangular Panels

Description: "A solution based upon small-deflection theory is presented for the critical shear stress of curved rectangular panels with simply supported edges. Computed curves which cover a wide range of panel dimensions are presented; these curves are found to be in good agreement with test results. Estimated curves are also given for panels with clamped edges" (p. 1).
Date: May 1947
Creator: Batdorf, S. B.; Stein, Manuel & Schildcrout, Murry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The determination of elastic stresses in gas-turbine disks

Description: Report presenting a method for the calculation of elastic stresses in symmetrical disks typical of those of a high-temperature gas turbine. Illustrative examples are presented to demonstrate how to treat solid disks, disks with central holes, and disks constructed of a single material or two or more welded materials.
Date: May 1947
Creator: Manson, S. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Distribution of bearing reactions on a rotating shaft supported on multiple journal bearings

Description: Report presenting an analytical treatment of the problem of determining the distribution of reaction forces among multiple plain bearings supporting a shaft subjected to rotating loads. An investigation conducted on a straight shaft operating in a seven-bearing crankcase of an aircraft engine is presented to show the importance of the hydrodynamic effect of the oil film.
Date: May 1947
Creator: Manson, S. S. & Morgan, W. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of spoiler-type lateral-control devices on the twisting moments of NACA 230-Series airfoil sections

Description: Report presenting an investigation of the effects of several spoiler arrangements on the spanwise variation of section twisting moments of a wing of NACA 230-series airfoil sections. Both plain and perforated spoilers were tested at a designated Mach and Reynolds number and force and moment measurements as well as chordwise pressure-distribution measurements at six spanwise stations were obtained.
Date: May 1947
Creator: Fitzpatrick, James E. & Furlong, G. Chester
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Mach Number and Reynolds Number on the Maximum Lift Coefficient of a Wing of NACA 230-Series Airfoil Sections

Description: Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps. Chordwise pressure-distribution measurements were made for all flap configurations.. Peak values of maximum lift coefficient were obtained at relatively low free-stream Mach numbers and, before critical Mach number was reached, were almost entirely dependent on Reynolds Number. Lift coefficient increased by increasing Mach number or deflecting flaps while critical pressure coefficient was reache… more
Date: May 1947
Creator: Furlong, G. Chester & Fitzpatrick, James E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Electrical Computer for the Solution of Shear-Lag and Bolted-Joint Problems

Description: "The analogy between the distribution of stresses in flat stiffened panels and the distribution of electric current in a ladder-type resistance network is used as the theoretical basis of an electrical computer for the rapid solution of shear-lag problems. The computer, consisting of variable resistors and multiple-current sources, is described; and typical examples are given of its use. The analogy is extended to include bolted-joint problems, and an example is given also" (p. 1).
Date: May 1947
Creator: Ross, Robert D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental and calculated characteristics of several NACA 44-series wings with aspect ratios of 8, 10, and 12 and taper ratios of 2.5 and 3.5

Description: The aerodynamic characteristics of seven unswept tapered wings were determined by calculation from two-dimensional data and by wind-tunnel tests in order to demonstrate the accuracy of the calculations and to show some of the effects of aspect ratio, taper ratio, and root thickness-chord ratio. The characteristics were calculated by the usual application of the lifting-line theory which assumes linear section lift curves and also by an application of the theory which allows the use of nonlinear… more
Date: May 1947
Creator: Neely, Robert H.; Bollech, Thomas V.; Westrick, Gertrude C. & Graham, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental determination of the damping in roll and aileron rolling effectiveness of three wings having 2 degree, 42 degree and 62 degree sweepback

Description: Report presenting tests to determine the damping in roll and aileron rolling effectiveness of three wings with different degrees of sweepback. The results showed that the values of damping in roll decreased with increasing sweepback. The rolling effectiveness of the aileron of the sweptback wing was found to be predicted with fair accuracy from static aileron-rolling-moment tests and wing-damping tests.
Date: May 1947
Creator: Bennett, Charles V. & Johnson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Exploratory Investigation of Laminar-Boundary-Layer Oscillations on a Rotating Disk

Description: Sinusoidal waves excited by random disturbances have been observed in the laminar boundary layer of a rotating disk at Reynolds numbers in a narrow range below the Reynolds number of transition. Their frequency was found to be approximately a constant times the velocity of the disk. The velocity of the waves at the radius of 11 inches was determined and found to be 0.2 linear velocity of the disk in a downstream direction, making an angle of approximately 14 degrees with the outward drawn radiu… more
Date: May 1947
Creator: Smith, Newell H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight investigation of the effects on airplane static longitudinal stability of a bungee and engine-tilt modifications

Description: Report presenting flight tests to evaluate an elevator stick-force bungee and engine tilt as methods of improving the longitudinal-control characteristics of an existing airplane. The stick-force bungee was found to be the simplest and most effective modification.
Date: May 1947
Creator: Rathert, George A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight tests of a double-hinged horizontal tail surface with reference to longitudinal-stability and control characteristics

Description: Report presenting testing of a double-hinged horizontal tail on a small low-speed airplane to determine the longitudinal stability and control characteristics. The flying characteristics of the airplane equipped with the double-hinged horizontal tail surface were generally satisfactory. The primary effect of removal of the elevator seal was a decrease in the elevator effectiveness.
Date: May 1947
Creator: Hanson, Carl M. & Anderson, Seth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight tests of an airplane model with 42 degree swetpback wing in the Langley free-flight tunnel

Description: Report presenting power-off flight tests in the free-flight tunnel to determine the dynamic stability characteristics of an airplane model with a 42 degree sweptback wing of aspect ratio 5.9 and taper ratio 0.5. The static-stability and wing-stall characteristics of the model were also determined. Results regarding force tests, flow surveys, and flight tests are provided.
Date: May 1947
Creator: Maggin, Bernard & Bennett, Charles V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight tests of an airplane model with a 62 degree swept-back wing in the Langley free-flight tunnel

Description: Report presenting a flight investigation in the free-flight tunnel to determine the severity of the dynamic stability and control problems associated with 62 degrees sweepback. In addition to the flight tests, force tests and tuft tests were made to determine the static-stability and wing-stall characteristics, and calculations were made to determine the boundary of zero damping of the lateral oscillation.
Date: May 1947
Creator: Maggin, Bernard & Bennett, Charles V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Friction Coefficients in a Vaneless Diffuser

Description: Note presenting a determination of friction coefficients for three constant-area vaneless diffusers, used in conjunction with a centrifugal impeller, from static- and total-pressure surveys taken at several radii and from the usual overall measurements of temperature, pressure, and air flow. The average value of the friction coefficient through the entire diffuser was approximately 50 percent higher than that for fully developed turbulent flow in smooth pipes.
Date: May 1947
Creator: Brown, W. Byron
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-scale investigation of the aerodynamic characteristics of a typical single-rotor helicopter in forward flight

Description: Report presenting an investigation of the forward-flight performance characteristics of a typical single-rotor helicopter equipped with main and tail rotors. Testing occurred over a range of tip-speed ratios and thrust coefficients. Results regarding the fuselage effects and rotor characteristics are provided.
Date: May 1947
Creator: Dingeldein, Richard C. & Schaefer, Raymond F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fundamentals of the Control of Gas-Turbine Power Plants for Aircraft, Part 3: Control of Jet Engines

Description: "The basic principles of the control of TL engines are developed on the basis of a quantitative investigation of the behavior of these behavior under various operating conditions with particular consideration of the simplifications permissible in each case. Various possible means of control of jet engines are suggested and are illustrated by schematic designs" (p. 1).
Date: May 1947
Creator: Kühl, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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