National Advisory Committee for Aeronautics (NACA) - 2,223 Matching Results

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A Study of the Motion and Aerodynamic Heating of Missiles Entering the Earth's Atmosphere at High Supersonic Speeds

Description: A simplified analysis of the velocity and deceleration history of missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.
Date: October 1957
Creator: Allen, H. Julian & Eggers, A. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Visualization study of secondary flows in turbine rotor tip regions

Description: Report presenting a visualization study using smoke to see the secondary-flow phenomena in the rotor-blade tip region of a low-speed turbine. Measurements of the factors affecting the flow patterns were recorded from visual observations. Results regarding a general description of the smoke patterns, shroud boundary-layer considerations, transition rotor tip speed, and high-speed-turbine operating conditions are provided.
Date: September 1955
Creator: Allen, Hubert W. & Kofskey, Milton G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Construction and Use of Charts in Design Studies of Gas Turbines

Description: "A method is presented for the computation and graphic representation of a series of possible turbine designs for any specific application. The use of a preliminary design chart is suggested for determining the number of stages and the effects of exit whirl and annular-area divergence on possible configurations. A specific design chart can then be made to aid in the study of the relations between turbine radius ratio, diameter, and significant design parameters such as Mach numbers, turning ang… more
Date: July 1951
Creator: Alpert, Sumner & Litrenta, Rose M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Comparison of the Turbulent Boundary-Layer Growth on an Unswept and a Swept Wing

Description: Note presenting an experimental investigation in which measurements were made of the turbulent boundary layer of a two-dimensional unswept wing and a comparable wing swept 45 degrees. The results indicate the applicability of simple sweep theory for determining turbulent boundary-layer growth on the swept wing for a lift coefficient of zero.
Date: September 1951
Creator: Altman, John M. & Hayter, Nora-Lee F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theory of helicopter damping in pitch or roll and a comparison with flight measurements

Description: Report presenting calculations and flight-test measurements on a single-main-rotor helicopter indicate that the damping moment about the helicopter center of gravity produced during pitching or rolling by a rotor which has flapping hinges on the rotor shaft, which depends primarily on four quantities: rotor speed, blade mass factor, height of the rotor hub above the helicopter center of gravity, and the ratio of collective pitch to the thrust coefficient - solidity ratio.
Date: October 1950
Creator: Amer, Kenneth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts for estimation of longitudinal-stability derivatives for a helicopter rotor in forward flight

Description: Report presenting charts to provide a convenient means for obtaining the derivatives of rotor resultant force, rotor pitching amount about the helicopter center of gravity, and rotor torque with respect to rotor angle of attack, forward speed, rotor speed, and collective pitch.
Date: March 1951
Creator: Amer, Kenneth B. & Gustafson, Frederic Bowen
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of the Experimental Pressure Distribution on an NACA 0012 Profile at High Speeds With That Calculated by the Relaxation Method

Description: Note presenting pressure-distribution measurements made on a 5-inch-chord NACA 0012 airfoil at zero angle of attack in the Langley rectangular high-speed tunnel, a 4- by 18-inch closed-throat tunnel, and compared with results calculated by Emmons for an equivalent airfoil-channel configuration by using the relaxation method.
Date: August 1950
Creator: Amick, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method of Selecting the Thickness, Hollowness, and Size of a Supersonic Wing for Least Drag and Sufficient Bending Strength at Specified Flight Conditions

Description: Note presenting a consideration of a wing-selection problem sometimes encountered in the preliminary design of supersonic airplanes and missiles. The problem is to determine the span, section thickness ratio, and skin thickness or hollowness ratio of the wing of least drag when the plan form, section shape, wing lift requirement, and flight conditions are assumed known. An example of the application of the method to a diamond wing at Mach number 2.0 for a range of specified flight conditions is… more
Date: July 1952
Creator: Amick, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Concentration on Ignition Delays for Various Fuel-Oxygen-Nitrogen Mixtures at Elevated Temperatures

Description: Note presenting measurements of ignition delays for mixtures of ethane, n-butane, isobutane, hydrogen, or propane with oxygen and nitrogen using a flow system with two experimental procedures. Delays were measured over a range of temperatures for each gas. Results regarding a comparison among fuels and effect of experimental procedure on absolute values of ignition delay are provided.
Date: December 1956
Creator: Anagnostou, E.; Brokaw, R. S. & Butler, J. N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compressive Crippling of Structural Sections

Description: "A method is presented for calculating crippling stresses of structural sections as a function of material properties and the proportions of the section. The presence of formed or anisotropic material is accounted for by the use of an effective stress-strain curve. The method of analysis applies to many sections for which a procedure for calculating crippling was not previously available" (p. 1).
Date: January 1956
Creator: Anderson, Melvin S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Local Instability of the Elements of a Truss-Core Sandwich Plate

Description: The charts presented give the compressive buckling coefficients for a single-truss-core and a double-truss-core sandwich plate. These charts cover a wide range of sandwich proportions and may be used for sandwiches with unequal faces. They apply to inplane compressive loads acting parallel or perpendicular to the core direction or for various combinations of these loads. (author).
Date: July 1958
Creator: Anderson, Melvin S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Research Results on Sandwich Structures

Description: "The results of compressive-buckling tests of steel sandwich plates are given, and the significant parameters which affect the strength of the plates are discussed. The various types of sandwich construction are shown to be comparable on a weight-strength basis with conventional high-strength aluminum-alloy construction" (p. 1).
Date: June 1957
Creator: Anderson, Melvin S. & Updegraff, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts Giving Critical Compressive Stress of Continuous Flat Sheet Divided Into Parallelogram-Shaped Panels

Description: "Charts giving the compressive-buckling stress coefficients for sheet panels of a shape occurring in swept-wing plan forms are presented. The panels are assumed to be a part of a continuous flat sheet divided by nondeflecting supports into parallelogram-shaped areas. The stability analysis was performed by the energy method and the results show that, over a wide range of panel aspect ratio, such panels are decidedly more stable than equivalent rectangular panels of the same area" (p. 1).
Date: July 1951
Creator: Anderson, Roger A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation of Crippling Strength of Plate Structures With Material Properties

Description: "A correlation approach to the crippling-strength analysis of plate structures in new materials and at elevated temperatures is presented. Appropriately defined crippling-strength moduli and correlation procedures are given for predicting the effect of a change in material properties on the strength of a structure. The strength moduli are readily calculated from the effective compressive stress-strain curve for the structural material" (p. 1).
Date: January 1956
Creator: Anderson, Roger A. & Anderson, Melvin S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts Relating the Compressive Buckling Stress of Longitudinally Supported Plates to the Effective Deflectional and Rotational Stiffness of the Supports

Description: Report presenting a stability analysis of a long flat rectangular plate subjected to uniform longitudinal compressive stress and support along its longitudinal edges and one or more other longitudinal lines by elastic line supports. This was performed in order to provide more information about stabilization methods for thin-wing construction. The effective stiffness of different supports and the buckling observed in different structures is provided.
Date: August 1953
Creator: Anderson, Roger A. & Semonian, Joseph W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Design Data for Multipost-Stiffened Wings in Bending

Description: From Summary: "The results of a computational program are presented which give numerical values of the stiffnesses required of the various components of a multipost-stiffened wing to achieve desired buckling-stress values under bending loads. Two arrangements of the posts are considered, upright posts and posts used as diagonals of a Warren truss. This work extends and summarizes the calculations presented in NACA RM L52K10a."
Date: January 1954
Creator: Anderson, Roger A.; Johnson, Aldie E., Jr. & Wilder, Thomas W., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of three design parameters on the operating characteristics of 75-millimeter-bore cylindrical roller bearings at high speeds

Description: Report presenting three experimental investigation conducted with 75-millimeter-bore cylindrical roller bearings to determine the effects of roller axial clearance ratio, cage diametral clearance ratio, and cage land width-diameter ratio on bearing operating temperatures, wear, cage slip, and high-speed operating characteristics.
Date: October 1956
Creator: Anderson, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of 110-millimeter-bore M-1 tool steel ball bearings at high speeds, loads, and temperatures

Description: Report presenting eleven 110-millimeter-bore ball thrust bearings made of M-1 tool steel were operated over a range of DN values at mean outer-race temperatures to 678 degrees Fahrenheit. Testing occurred at a variety of thrust loads, radial loads, oil flows, and oil inlet temperatures. Results regarding the difference between tests without heat addition and tests with heat addition, fatigue failures, performance of cage materials, and oil-interruption tests are provided.
Date: January 1957
Creator: Anderson, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Turbulent Shearing Stress in the Boundary Layer of Yawed Flat Plates

Description: Note presenting hot-wire anemometer measurements of the turbulent shearing stress in a turbulent boundary layer on a yawed flat plate. The measured velocity profiles are used to calculate the shear distribution and the result is compared with the result of experimental shear measurements.
Date: April 1958
Creator: Ashkenas, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Turbulent Boundary Layer on a Yawed Flat Plate

Description: Note presenting the problem of the effect of yaw on the turbulent boundary layer and skin friction of infinite cylinders, which is reviewed and compared with the case of laminar flow. The conclusion indicates that present understanding of the mechanism of turbulent shear does not permit exhaustion of two-dimensional data even to this elementary case of three-dimensional flow. Results regarding pressure distributions, two-dimensionality and flow direction, velocity profiles, virtual origin, virt… more
Date: April 1955
Creator: Ashkenas, Harry & Riddell, Frederick R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Operating Characteristics of an Acceleration Restrictor as Determined by Means of a Simulator

Description: Note presenting the operating characteristics of an acceleration restrictor which limits the normal acceleration of an airplane in maneuvers determined from tests on a simulator. The simulator consisted of a control stick geared to a magnetic brake unit and an analog computer which simulated the dynamic characteristics of the airplane.
Date: December 1954
Creator: Assadourian, Arthur
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat-Capacity Measurements of Titanium and of a Hydride of Titanium for Temperatures From 4 to 15 K Including a Detailed Description of a Special Adiabatic Specific-Heat Calorimeter

Description: Note presenting a description of an adiabatic specific-heat calorimeter bridging the interval between 4 and 15 degrees Kelvin temperatures. The instrument uses a constant-volume helium gas thermometer as the working thermometer. The instrument is tested on an alloy and a sample of pure titanium and the results are described.
Date: October 1956
Creator: Aven, M. H.; Craig, R. S. & Wallace, W. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a Slat in Several Different Positions on an NACA 64A010 Airfoil for a Wide Range of Subsonic Mach Numbers

Description: Report presenting the two-dimensional aerodynamic characteristics of an NACA 64A010 airfoil with a slat at a range of Mach numbers. Two types of slat positions were investigated, one with the slat leading edge extended forward along the airfoil chord line and one with the slat extended forward and displaced below the chord line. Results regarding lift, drag, pitching moment, and pressure distribution are provided.
Date: March 1954
Creator: Axelson, John A. & Stevens, George L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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