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Icing Limit and Wet-Surface Temperature Variation for Two Airfoil Shapes Under Simulated High-Speed Flight Conditions

Description: Note presenting an experimental study of the wet-surface temperature and stream conditions that result in ice-free surfaces for bodies in flight through icing clouds, and the results obtained are compared with values calculated using an analytical method. Two symmetrical airfoil models, one of diamond shape and the other of double-circular-arc contour, were used in the investigation. Results regarding the chordwise variation of pressure distribution, chordwise variation of recovery factor, the … more
Date: February 1955
Creator: Coles, Willard D.
Partner: UNT Libraries Government Documents Department
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A Fibrous-Glass Compact as a Permeable Material for Boundary-Layer-Control Applications Using Area Suction

Description: "Measurements were made of the resistance of fibrous-glass compacts to normal air flow. The flow resistance was related to the thickness and density. As a porous material for boundary-layer-control applications using area suction, the fibrous-glass compact could be made to any desired thickness and permeability and sandwiched between perforated rigid surfaces" (p. 1).
Date: January 1955
Creator: Dannenberg, Robert E.; Weiberg, James A. & Gambucci, Bruno J.
Partner: UNT Libraries Government Documents Department
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Variation of Local Liquid-Water Concentration About an Ellipsoid of Fineness Ratio 10 Moving in a Droplet Field

Description: From Summary: "Trajectories of water droplets about an ellipsoid of revolution with a fineness ratio of 10 (10 percent thick) in flight through a droplet field were computed with the aid of a differential analyzer. Analyses of these trajectories indicate that the local concentration of liquid water at various points about an ellipsoid varies considerably and under some conditions may be several times the free-stream concentration. Curves of the local concentration factor as a function of spatia… more
Date: April 1955
Creator: Brun, Rinaldo J. & Dorsch, Robert G.
Partner: UNT Libraries Government Documents Department
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A Dye-Tracer Technique for Experimentally Obtaining Impingement Characteristics of Arbitrary Bodies and a Method for Determining Droplet Size Distribution

Description: "A dye-tracer technique has been developed whereby the quantity of dyed water collected on a blotter-wrapped body exposed to an air stream containing a dyed-water spray cloud can be colorimetrically determined in order to obtain local collection efficiencies, total collection efficiency, and rearward extent of impingement on the body. In addition, a method has been developed whereby the impingement characteristics obtained experimentally for a body can be related to theoretical impingement data… more
Date: March 1955
Creator: von Glahn, Uwe H.; Gelder, Thomas F. & Smyers, William H., Jr.
Partner: UNT Libraries Government Documents Department
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Impingement of Water Droplets on a Sphere

Description: Droplet trajectories about a sphere in ideal fluid flow were calculated. From the calculated droplet trajectories the droplet impingement characteristics of the sphere were determined. Impingement data and equations for determining the collection efficiency, the area, and the distribution of impingement are presented in terms of dimensionless parameters. The range of flight and atmospheric conditions covered in the calculations was extended considerably beyond the range covered by previously re… more
Date: November 1955
Creator: Dorsch, Robert G.; Saper, Paul G. & Kadow, Charles F.
Partner: UNT Libraries Government Documents Department
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Impingement of water droplets on NACA 65A004 airfoil at 0 degrees angle of attack

Description: From Summary: "The trajectories of water droplets in the air flowing past an NACA 6511004 airfoil at a n angle of attack of 0 deg were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented t o cover a large range of flight and atmospheric conditions. These impingement characteristics are compared briefly with those pre… more
Date: November 1955
Creator: Brun, Rinaldo J. & Vogt, Dorothea E.
Partner: UNT Libraries Government Documents Department
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Quasi-Cylindrical Theory of Wing-Body Interfernece at Supersonic Speeds and Comparison With Experiment

Description: Report presenting a theoretical method for calculating the flow field about a wing-body combination employing bodies deviating only slightly in shape from a circular cylinder. The method is applied to the calculation of the pressure field acting between a circular cylindrical body and a rectangular wing.
Date: 1955
Creator: Nielsen, Jack Norman
Partner: UNT Libraries Government Documents Department
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Effect of Dissociation on Thermodynamic Properties of Pure Diatomic Gases

Description: A graphical method is described by which the enthalpy, entropy, and compressibility factor for the equilibrium mixture of atoms and diatomic molecules for pure gaseous elements may be obtained and shown for any dissociating element for which the necessary data exist. Results are given for hydrogen, oxygen, and nitrogen. The effect of dissociation on the heat capacity is discussed briefly.
Date: April 1955
Creator: Woolley, Harold W.
Partner: UNT Libraries Government Documents Department
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Axially Symmetric Shapes With Minimum Wave Drag

Description: Report presenting external wave drag of bodies of revolution moving at supersonic speeds, which can be expressed either in terms of the geometry of the body or in terms of the body-simulating axial source distribution. The second of the methods is found to be more tractable.
Date: February 1955
Creator: Heaslet, Max A. & Fuller, Franklyn B.
Partner: UNT Libraries Government Documents Department
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Cooperative Investigation of Relationship Between Static and Fatigue Properties of Wrought N-155 Alloy at Elevated Temperatures

Description: Note presenting extensive data relating properties of wrought N-155 alloy under static, combined static and dynamic, and completed reversed dynamic stress conditions. Time periods for fracture ranged from 50 to 500 hours at room temperatrue, 1000, 1200, 1350, and 1500 degrees Fahrenheit. Results regarding the rupture and fatigue strengths, fatigue strengths based on cycles to failure, influence of superimposed fatigue loads on creep, influence on superimposed fatigue stress on elongation in the… more
Date: April 1955
Creator: NACA Subcommittee on Heat-Resisting Materials
Partner: UNT Libraries Government Documents Department
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Second Order Subsonic Airfoil-Section Theory and Its Practical Application

Description: Note presenting several recent advances in plane subsonic flow theory combined into a unified second-order theory for airfoils of arbitrary shape. The solution is reached in three steps. Solutions for a number of airfoils are given and are compared with the results of other theories and of the experiment.
Date: March 1955
Creator: Van Dyke, Milton D.
Partner: UNT Libraries Government Documents Department
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Boundary lubrication of steel with fluorine- and chlorine-substituted methane and ethane gases

Description: Report presenting a study of the lubrication of steel by a series of stable fluorine- and chlorine-substituted methane and ethane derivatives. Several compounds containing fluorine and two or more chlorine atoms per molecule functioned as boundary lubricants to reduce friction and to prevent surface welding and metal transfer.
Date: February 1955
Creator: Murray, S. F.; Johnson, Robert L. & Swikert, Max A.
Partner: UNT Libraries Government Documents Department
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Free-flight measurements of turbulent-boundary-layer skin friction in the presence of severe aerodynamic heating at Mach numbers from 2.8 to 7.0

Description: Report presenting experimental measurements of average skin friction of the turbulent boundary layer on free-flying, hollow-cylinder models at four Mach numbers at conditions of high rates of heat transfer. The data of the investigation indicates that increasing skin-friction ratio with increasing heat-transfer rates will persist up to Mach numbers as high as 7. Results regarding skin-friction ratio and the T' method for evaluating skin friction are provided.
Date: March 1955
Creator: Sommer, Simon C. & Short, Barbara J.
Partner: UNT Libraries Government Documents Department
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A Note on the Drag Due to Lift of Rectangular Wings of Low Aspect Ratio

Description: Note presenting some methods of estimating the induced drag of low-aspect-ratio wings, which are discussed and compared with experiments. The profile drag due to lift is also discussed and a method is developed which relates the effect of aspect ratio on the profile drag due to lift to an "effective" two-dimensional lift coefficient.
Date: January 1955
Creator: Polhamus, Edward C.
Partner: UNT Libraries Government Documents Department
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Analytical determination of effect of water injection on power output of turbine-propeller engine

Description: From Introduction: "References 1 and 2 indicate that the sea-level static thrust of a centrigual-flow-type turbojet engine may be increased about 25 percent by use of liquid injection. Reference 3 indicates that greater thrust augmentation is possible at a compressor pressure ratio of 11 than of 4."
Date: March 1955
Creator: Ross, Albert O. & Huppert, Merle C.
Partner: UNT Libraries Government Documents Department
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Two Miniature Temperature Recorders for Flight Use

Description: Report presenting the description and characteristics of two small temperature recorders suitable for flight use. One recorder is an electro-mechanical followup, self-balancing potentiometer type and one obtains self-balance by using an electronic feedback amplifier.
Date: April 1955
Creator: Foster, John V.
Partner: UNT Libraries Government Documents Department
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Similar Solutions for the Compressible Laminar Boundary Layer with Heat Transfer and Pressure Gradient

Description: Note applying Stewartson's transformation to the laminar compressible boundary-layer equations and the requirement of similarity, resulting in a set of ordinary nonlinear differential equations previously quoted by Stewartson, but unsolved. The requirements of the system are specified. It is then transformed to an integral system with the velocity ratio as the independent variable.
Date: February 1955
Creator: Cohen, Clarence B. & Reshotko, Eli
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of the Base Pressure Characteristics of Nonlifting Bodies of Revolution at Mach Numbers From 2.73 to 4.98

Description: Report presenting an investigation in the supersonic wind tunnel to determine some of the base pressure characteristics of related bodies of revolution at zero angle of attack. Results regarding variation of pressure over the base, variation of base pressure with Reynolds number, effect of nose and afterbody shapes, variation of base pressure with Mach number, and correlation of base pressure data are provided.
Date: March 17, 1955
Creator: Reller, John O., Jr. & Hamaker, Frank M.
Partner: UNT Libraries Government Documents Department
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The compressible laminar boundary layer with heat transfer and arbitrary pressure gradient

Description: Report presenting an approximate method for the calculation of the compressible laminar boundary layer with heat transfer and arbitrary pressure gradient, based on Thwaites' correlation concept. The method results from the application of Stewartson's transformation to Prandtl's equations, which yields a nonlinear set of two first-order differential equations. Calculations of an example show that the method is reliable when compared with the perturbation method over the same range of Mach number… more
Date: April 1955
Creator: Cohen, Clarence B. & Reshotko, Eli
Partner: UNT Libraries Government Documents Department
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Low-Speed Investigation of the Effects of Angle of Attack on the Pressure Recovery of a Circular Nose Inlet With Several Lip Shapes

Description: Note presenting wind-tunnel tests to ascertain the total-pressure recovery of a circular nose inlet utilizing various shapes of inlet lips. The tests were conducted at a free-stream Mach number of 0.237 with inlet flows ranging from low values to choking and at angles of attack from 0 to 25 degrees.
Date: May 1955
Creator: Blackaby, James R.
Partner: UNT Libraries Government Documents Department
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Some Considerations on Two-Dimensional Thin Airfoils Deforming in Supersonic Flow

Description: "The aerodynamic characteristics of indicially cambered two-dimensional airfoils in supersonic flow are determined theoretically. These indicial functions are used to determine the power required to sustain a general time-varying chordwise deformation. The harmonically oscillating parabolic mode is considered in detail and stability boundaries are presented for this case" (p. 1).
Date: January 1955
Creator: Migotsky, Eugene
Partner: UNT Libraries Government Documents Department
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