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Theoretical study of the lateral frequency response to gusts of a fighter airplane, both with controls fixed and with several types of autopilots

Description: Report presenting a theoretical approach to determine the lateral frequency response of a fighter airplane to side gusts and rolling gusts at a Mach number of 0.7 and an altitude of 30,000 feet. Frequency response and power spectral density were determined with the controls fixed and in combination with three different basic types of attitude autopilots.
Date: March 1956
Creator: Adams, James J. & Mathews, Charles W.
Item Type: Refine your search to only Report
open access

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
open access

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
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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
open access

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
open access

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
open access

Properties of aircraft fuels

Description: Report presenting a combination of two previously published reports with an extension of the data to cover properties of fuels up to temperatures as high as 400 degrees Fahrenheit.
Date: August 1956
Creator: Barnett, Henry C. & Hibbard, Robert R.
Item Type: Refine your search to only Report
open access

Lift and moment coefficients for an oscillating rectangular wing-aileron configuration in supersonic flow

Description: Report presenting the use of linearized theory for compressible unsteady flow to treat the problem of a partial-span rectangular control surface hinged at its leading edge and mounted on a rectangular wing, oscillating in supersonic flow. The motions of the wing-aileron configuration are assumed to consist of vertical translation, pitching, and aileron rotation. Results regarding the spanwise aerodynamic effects and application to flutter are provided.
Date: July 1956
Creator: Berman, Julian H.
Item Type: Refine your search to only Report
open access

Exploratory investigation of boundary-layer transition on a hollow cylinder at a Mach number of 6.9

Description: Report presenting an investigation of the Reynolds number for transition on the outside of a hollow cylinder with heat transfer from the boundary layer to the wall at Mach number 6.9. At a given Mach number, it appears that the Reynolds number based on leading-edge thickness is an important parameter in comparisons of flat-plate transition data from various installations.
Date: May 1956
Creator: Bertram, Mitchel H.
Item Type: Refine your search to only Report
open access

Linearized Lifting-Surface and Lifting-Line Evaluations of Sidewash Behind Rolling Triangular Wings at Supersonic Speeds

Description: Note presenting the lifting-surface sidewash behind rolling triangular wings for a range of supersonic Mach numbers for which the wing leading edges remain swept behind the Mach cone emanating from the wing apex. Variations of the sidewash with longitudinal distance in the vertical plane of symmetry are presented in graphical form.
Date: March 1956
Creator: Bobbitt, Percy J.
Item Type: Refine your search to only Report
open access

Interaction of Bearing and Tensile Loads on Creep Properties of Joints

Description: The interaction of bearing and tensile loads on the creep behavior of joints was studied. A specimen was designed for this study which possessed some of the general features of pin and rivet joint connections and an apparatus was constructed to apply both bearing and tensile loads to the joint model. Deformation measurements were made by use of a photogrid printed on the joint model.
Date: October 1956
Creator: Bodine, E. G.; Carlson, R. L. & Manning, G. K.
Item Type: Refine your search to only Report
open access

Effect of pneumatic de-icers and ice formations on aerodynamic characteristics of a airfoil

Description: Report presenting measurements of lift, drag, and pitching moment of an NACA 0011 airfoil in icing using two types of pneumatic de-icers, one with spanwise inflatable tubes and the other with chordwise tubes. Results regarding the airfoil characteristics with the de-icer operating and effect of primary ice formation on drag, lift, and pitch with the de-icer inoperative are provided.
Date: February 1956
Creator: Bowden, Dean T.
Item Type: Refine your search to only Report
open access

Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0

Description: Note presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.
Date: August 1956
Creator: Brajnikoff, George B. & Rogers, Arthur W.
Item Type: Refine your search to only Report
open access

Turbulent-Heat-Transfer Measurements at a Mach Number of 3.90

Description: Report presenting turbulent-heat-transfer measurements obtained through the use of an axially symmetric annual nozzle consisting of an inner shaped center body and an outer cylindrical sleeve at Mach number 3.90. Results regarding the variation of wall temperature with longitudinal distance, variation of local Nusselt number with local Reynolds number, and variation of local temperature-recovery factor with local Reynolds number are provided.
Date: July 1956
Creator: Brevoort, Maurice J.
Item Type: Refine your search to only Report
open access

Effect of leading-edge geometry on boundary-layer transition at Mach 3.1

Description: Report presenting the effect of leading-edge geometry on transition position, recovery-factor distribution, boundary-layer profile, and the roughness required to induce transition at Mach number 3.1 for a hollow cylinder aligned with the air stream. Results regarding leading-edge effect, roughness elements in laminary boundary layer, surface-heat condition effects, and effect of stream total temperature are provided.
Date: March 1956
Creator: Brinich, Paul F.
Item Type: Refine your search to only Report
open access

Investigation at Supersonic Speeds of the Variation With Reynolds Number and Mach Number of the Total, Base, and Skin-Friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag

Description: Results are presented from an investigation of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag of seven boattail bodies of revolution designed for minimum wave drag according to the theory of NACA-TN-2550. The tests covered a Reynolds number range from approximately 1.0 x 10(6) to 10.0 x 10(6) at Mach numbers of 1.62, 1.93, and 2.41 respectively.
Date: June 1956
Creator: Bromm, August F., Jr. & Goodwin, Julia M.
Item Type: Refine your search to only Report
open access

Analytical determination of the natural coupled frequencies and mode shapes and the response to oscillating forcing functions of tandem helicopters

Description: Report presenting a method for the analytical determination of the natural coupled frequencies and mode shapes of vibrations in the vertical plane of tandem helicopters. That information is then used to calculate the response of the helicopter to applied oscillation forces. Calculated response curves show how the vibrations of the cockpit vary with frequency and method of application of oscillating forces applied at the hubs.
Date: December 1956
Creator: Brooks, George W. & Houbolt, John C.
Item Type: Refine your search to only Report
open access

Preliminary wind-tunnel tests of triangular and rectangular wings in steady roll at Mach numbers of 1.62 and 1.92

Description: Damping-in-roll coefficients for a series of triangular plan-form wings and two rectangular plan-form wings have been obtained from supersonic-tunnel tests. The wings were mounted on a body of revolution and tested at Mach numbers of 1.62 and 1.92.
Date: June 1956
Creator: Brown, Clinton E. & Heinke, Harry S., Jr.
Item Type: Refine your search to only Report
open access

Cloud-droplet ingestion in engine inlets with inlet velocity ratios of 1.0 and 0.7

Description: Report presenting the paths of cloud droplets into two engine inlets for a wide range of meteorological and flight conditions. The amount of water in droplet form ingested by the inlets and the amount and distribution of water impinging on the inlet walls is obtained from droplet-trajectory configurations. Results regarding an inlet with velocity ratio of 1.0 and a ratio of 0.7 are provided.
Date: January 1956
Creator: Brun, Rinaldo J.
Item Type: Refine your search to only Report
open access

A Self-Balancing Line-Reversal Pyrometer

Description: Report presenting a description of a pyrometer that is self-balancing and is able to replace the two conventional manual operations of the line-reversal method. A description of the operation of the pyrometer and the performance and results are provided.
Date: August 1956
Creator: Buchele, Donald
Item Type: Refine your search to only Report
open access

A method for calculating the contour of bodies of revolution with a prescribed pressure gradient at supersonic speed with experimental verification

Description: Report presenting a method to compute the contour of a body for a prescribed pressure distribution based on the theory of characteristics. A mode was constructed with an initial included cone angle of 30 degrees and a contour to give a linear pressure distribution for a free-stream Mach number of 3.13.
Date: March 1956
Creator: Burbank, Paige B.
Item Type: Refine your search to only Report
open access

Theoretical wave drag of shrouded airfoils and bodies

Description: Formulas for the wave drag of shrouded symmetrical airfoils and shrouded bodies of revolution of arbitrary shape are derived by means of linearized theory. In the case of the airfoils, the shroud consists of flat plates and for the bodies of revolution the shroud is a cylindrical shell. The results obtained hold for a Mach number range dependent on the geometry of the configuration. Expressions are also given for determining a class of body shapes for which the wave drag is theoretically zero.
Date: June 1956
Creator: Byrd, Paul F.
Item Type: Refine your search to only Report
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