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Boron and zirconium from crucible refractories in a complex heat-resistant alloy

Description: In a laboratory study of the factors involved in the influence of induction vacuum melting on 55ni-20cr-15co-4mo-3ti-3al heat resistant alloy, it was found that the major factor was the type of ceramic used as the crucible. The study concluded that trace amounts of boron or zirconium derived from reaction of the melt with the crucible refactories improved creep-rupture properties at 1,600 degrees F. Boron was most effective and, in addition, markedly improved hot-workability.
Date: August 5, 1958
Creator: Decker, R. F.; Rowe, John P. & Freeman, J. W.
Partner: UNT Libraries Government Documents Department
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Characteristics of the Langley 8-Foot Transonic Tunnel With Slotted Test Section

Description: "A large wind tunnel, approximately 8 feet in diameter, has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of such a slotted wind tunnel, already known with respect to the reduction of the subsonic blockage interference and the production of continuously variable supersonic flows, has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality could be produced. Experimental l… more
Date: July 3, 1958
Creator: Wright, Ray H.; Ritchie, Virgil S. & Pearson, Albin O.
Partner: UNT Libraries Government Documents Department
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Measurements of free-space oscillating pressures near propellers at flight Mach numbers to 0.72

Description: "In the course of a short flight program initiated to check the theory of Garrick and Watkins (NACA rep. 1198), a series of measurements at three stations were made of the oscillating pressures near a tapered-blade plan-form propeller and rectangular-blade plan form propeller at flight Mach numbers up to 0.72. In contradiction to the results for the propeller studied in NACA rep. 1198, the oscillating pressures in the plane ahead of the propeller were found to be higher than those immediately b… more
Date: July 1, 1958
Creator: Kurbjun, Max C. & Vogeley, Arthur W.
Partner: UNT Libraries Government Documents Department
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Area-Suction Boundary-Layer Control as Applied to the Trailing-Edge Flaps of a 35 Degree Swept-Wing Airplane

Description: "A wind-tunnel investigation was made to determine the effects on the aerodynamic characteristics of a 35 degree swept-wing airplane of applying area-suction boundary-layer control to the trailing-edge flaps. Flight tests of a similar airplane were then conducted to determine the effect of boundary-layer control in the handling qualities and operation of the airplane, particularly during landing. The wind-tunnel and flight tests indicated that area suction applied to the trailing-edge flaps pro… more
Date: May 6, 1958
Creator: Cook, Woodrow L.; Anderson, Seth B. & Cooper, George E.
Partner: UNT Libraries Government Documents Department
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Blowing-type boundary-layer control as applied to the trailing-edge flaps of a 35 degree swept-wing airplane

Description: A wind-tunnel investigation was made to determine the effects on the aerodynamic characteristics of a 35 degree swept-wing airplane of applying blowing-type boundary-layer control to the trailing-edge flaps. Flight tests of a similar airplane were then conducted to determine the effects of boundary-layer control on the handling qualities and operation of the airplane, particularly during landing and take-off. The wind-tunnel and flight tests indicated that blowing over the flaps produced large … more
Date: April 30, 1958
Creator: Kelly, Mark W.; Anderson, Seth B. & Innis, Robert C.
Partner: UNT Libraries Government Documents Department
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Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds

Description: The performance of NACA 65-series compressor blade section in cascade has been investigated systematically in a low-speed cascade tunnel. Porous test-section side walls and for high-pressure-rise conditions, porous flexible end walls were employed to establish conditions closely simulating two-dimensional flow. Blade sections of design lift coefficients from 0 to 2.7 were tested over the usable angle-of-attack range for various combinations of inlet-flow angle. A sufficient number of combinatio… more
Date: January 31, 1958
Creator: Emery, James C.; Herrig, L. Joseph; Erwin, John R. & Felix, A. Richard
Partner: UNT Libraries Government Documents Department
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A Correlation of Results of Flight Investigation With Results of an Analytical Study of Effects of Wing Flexibility on Wing Strains Due to Gusts

Description: An analytical study of the effects of wing flexibility on wing strains due to gusts has been made for four spanwise stations of a four-engine bomber airplane, and the results have been correlated with results of a previous flight investigation.
Date: 1958
Creator: Shufflebarger, C. C.; Payne, Chester B. & Cahen, George L.
Partner: UNT Libraries Government Documents Department
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A Low-Speed Experimental Investigation of the Effect of a Sandpaper Type of Roughness on Boundary-Layer Transition

Description: Report describing the effects of an area of roughness on the velocity and turbulence measurements of an airfoil. It details the effects of the size, location, and height of the roughness on the Reynolds number. From Summary: "An investigation was made in the Langley low-turbulence pressure tunnel to determine the effect of size and location of a sandpaper type of roughness on the Reynolds number for transition."
Date: 1958
Creator: Horton, Elmer A. & von Doenhoff, Albert E.
Partner: UNT Libraries Government Documents Department
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NACA Research on Slurry Fuels

Description: "An extensive program was conducted to investigate the use of concentrated slurries of boron and magnesium in liquid hydrocarbon as fuels for afterburners and ramjet engines. Analytical calculations indicated that magnesium fuel would give greater thrust and that boron fuel would give greater range than are obtainable from jet hydrocarbon fuel alone. It was hoped that the use of these solid elements in slurry form would permit the improvement to be obtained without requiring unconventional fuel… more
Date: 1958
Creator: Pinns, M. L.; Olson, W. T.; Barnett, H. C. & Breitwieser, R.
Partner: UNT Libraries Government Documents Department
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Thin airfoil theory based on approximate solution of the transonic flow equation

Description: A method is presented for the approximate solution of the nonlinear equations of transonic flow theory. Solutions are found for two-dimensional flows at a Mach number of 1 and for purely subsonic and purely supersonic flows. Results are obtained in closed analytic form for a large and significant class of nonlifting airfoils. At a Mach number of 1 general expressions are given for the pressure distribution on an airfoil of specified geometry and for the shape of an airfoil having a prescribed p… more
Date: 1958
Creator: Spreiter, John R. & Alksne, Alberta Y.
Partner: UNT Libraries Government Documents Department
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Drag Minimization for Wings and Bodies in Supersonic Flow

Description: "The minimization of inviscid fluid drag is studied for aerodynamic shapes satisfying the conditions of linearized theory, and subject to imposed constraints on lift, pitching moment, base area, or volume. The problem is transformed to one of determining two-dimensional potential flows satisfying either Laplace's or Poisson's equations with boundary values fixed by the imposed conditions. A general method for determining integral relations between perturbation velocity components is developed. … more
Date: November 29, 1957
Creator: Heaslet, Max A. & Fuller, Franklyn B.
Partner: UNT Libraries Government Documents Department
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Effect of fuel variables on carbon formation in turbojet-engine combustors

Description: Report presents the results of an investigation of the effects of fuel properties and of a number of fuel additives on combustion-chamber carbon deposition and exhaust-gas smoke formation in a single tubular turbojet-engine combustor. Limited tests were conducted with a number of the fuels in several full-scale turbojet engines to verify single-combustor data.
Date: October 23, 1957
Creator: Jonash, Edmund R.; Wear, Jerrold D. & Cook, William P.
Partner: UNT Libraries Government Documents Department
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Investigation of a nonlinear control system

Description: A discontinuous variation of coefficients of the differential equation describing the linear control system before nonlinear elements are added is studied in detail. The nonlinear feedback is applied to a second-order system. Simulation techniques are used to study performance of the nonlinear control system and to compare it with the linear system for a wide variety of inputs. A detailed quantitative study of the influence of relay delays and of a transport delay is presented.
Date: October 18, 1957
Creator: Flügge-Lotz, I.; Taylor, C. F. & Lindberg, H. E.
Partner: UNT Libraries Government Documents Department
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Growth of Disturbances in a Flame-Generated Shear Region

Description: Results are presented of an experimental and theoretical investigation of the growth of transverse velocity disturbances in the shear region caused by a flame in a duct. In the theoretical stability analysis, a flow field arising from a flame in a duct was analyzed. The flow was neutrally stable to symmetric disturbances and unstable to antisymmetric ones. In the experimental part of the program disturbances of various frequencies were imposed on a flame stabilized in a duct, and the effects we… more
Date: October 14, 1957
Creator: Blackshear, Perry L., Jr.
Partner: UNT Libraries Government Documents Department
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Relation of Turbojet and Ramjet Combustion Efficiency to Second-Order Reaction Kinetics and Fundamental Flame Speed

Description: Theoretical studies of the turbojet and ramjet combustion process are summarized and the resulting equations are applied to experimental data obtained from various combustor tests. The theoretical treatment assumes that one step in the over-all chain of processes which constitute jet-engine combustion is sufficiently slow to be the rate-controlling step that determines combustion efficiency.
Date: August 5, 1957
Creator: Childs, J. Howard; Reynolds, Thaine W. & Graves, Charles C.
Partner: UNT Libraries Government Documents Department
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Elliptic Cones Alone and with Wings at Supersonic Speed

Description: "To help fill the gap in the knowledge of aerodynamics of shapes intermediate between bodies of revolution and flat triangular wings, force and moment characteristics for elliptic cones have been experimentally determined for Mach numbers of 1.97 and 2.94. Elliptic cones having cross-sectional axis ratios from 1 through 6 and with lengths and base areas equal to circular cones of fineness ratios 3.67 and 5 have been studied for angles of bank of 0 degree and 90 degrees. Elliptic and circular co… more
Date: July 17, 1957
Creator: Jorgensen, Leland H.
Partner: UNT Libraries Government Documents Department
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The Mechanism of Thermal-Gradient Mass Transfer in the Sodium Hydroxide-Nickel System

Description: "Thermal-gradient mass transfer" was investigated in the molten sodium hydroxide-nickel system. Possible mechanisms (physical, electrochemical, and chemical) are discussed in terms of experimental and theoretical evidence. Experimental details are included in appendixes.
Date: June 20, 1957
Creator: May, Charles E.
Partner: UNT Libraries Government Documents Department
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A Method of Computing the Transient Temperature of Thick Walls From Arbitrary Variation of Adiabatic-Wall Temperature and Heat-Transfer Coefficient

Description: "A method of calculating the temperature of thick walls has been developed in which the time series and the response to a unit triangle variation of surface temperature concepts are used, together with essentially standard formulas for transient temperature and heat flow into thick walls. The method can be used without knowledge of the mathematical tools of its development. The method is particularly suitable for determining the wall temperature in one-dimensional thermal problems in aeronautic… more
Date: June 18, 1957
Creator: Hill, P. R.
Partner: UNT Libraries Government Documents Department
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Calculated and Measured Stresses in Simple Panels Subject to Intense Random Acoustic Loading Including the Near Noise Field of a Turbojet Engine

Description: "Flat 2024-T3 aluminum panels measuring 11 inches by 13 inches were tested in the near noise fields of a 4-inch air jet and turbojet engine. The stresses which were developed in the panels are compared with those calculated by generalized harmonic analysis. The calculated and measured stresses were found to be in good agreement. In order to make the stress calculations, supplementary data relating to the transfer characteristics, damping, and static response of flat and curved panels under peri… more
Date: June 3, 1957
Creator: Lassiter, Leslie W. & Hess, Robert W.
Partner: UNT Libraries Government Documents Department
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Approximate analysis of effects of large deflections and initial twist on torsional stiffness of a cantilever plate subjected to thermal stresses

Description: From Summary: "An approximate analysis of the nonlinear effects of initial twist and large deflections on the torsional stiffness of a cantilever plate subjected to a nonuniform temperature distribution is presented. The Von Karman large-deflection equations are satisfied through the use of a variational principle. The results show that initial twist and applied moments can have significant effects on the changes in stiffness produced by nonuniform heating, particularly in the region of the buc… more
Date: May 15, 1957
Creator: Heldenfels, Richard R. & Vosteen, Louis F.
Partner: UNT Libraries Government Documents Department
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Survey of hydrogen combustion properties

Description: This literature digest of hydrogen-air combustion fundamentals presents data on flame temperature, burning velocity, quenching distance, flammability limits, ignition energy, flame stability, detonation, spontaneous ignition, and explosion limits. The data are assessed, recommended values are given, and relations among various combustion properties are discussed. New material presented includes: theoretical treatment of variation in spontaneous ignition lag with temperature, pressure, and compo… more
Date: April 26, 1957
Creator: Drell, Isadore L. & Belles, Frank E.
Partner: UNT Libraries Government Documents Department
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Compressible Laminar Boundary Layer Over a Yawed Infinite Cylinder With Heat Transfer and Arbitrary Prandtl Number

Description: "The equations are presented for the development of the compressible laminar boundary layer over a yawed infinite cylinder. For compressible flow with a pressure gradient the chordwise and spanwise flows are not independent. Using the Stewartson transformation and a linear viscosity-temperature relation yields a set of three simultaneous ordinary differential equations in a form yielding similar solutions. These equations are solved for stagnation-line flow for surface temperatures from zero to… more
Date: April 4, 1957
Creator: Reshotko, Eli & Beckwith, Ivan E.
Partner: UNT Libraries Government Documents Department
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On flow of electrically conducting fluids over a flat plate in the presence of a transverse magnetic field

Description: The use of a magnetic field to control the motion of electrically conducting fluids is studied. The incompressible boundary-layer solutions are found for flow over a flat plate when the magnetic field is fixed relative to the plate or to the fluid. The equations are integrated numerically for the effect of the transverse magnetic field on the velocity and temperature profiles, and hence, the skin friction and rate of heat transfer. It is concluded that the skin friction and the heat-transfer ra… more
Date: March 13, 1957
Creator: Rossow, Vernon J.
Partner: UNT Libraries Government Documents Department
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A variational theorem for creep with applications to plates and columns

Description: A variational theorem is presented for a body undergoing creep. Solutions to problems of the creep behavior of plates, columns, beams, and shells can be obtained by means of the direct methods of the calculus of variations in conjunction with the stated theorem. The application of the theorem is illustrated for plates and columns by the solution of two sample problems.
Date: March 5, 1957
Creator: Sanders, J. Lyell, Jr.; McComb, Harvey G., Jr. & Schlechte, Floyd R.
Partner: UNT Libraries Government Documents Department
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