National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

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Low tire friction and cornering forces on a wet surface

Description: Report presenting an investigation to study typical tire behavior on wet runways, to determine the mechanisms by which water on runways reduced tire forces, and to determine the extent of this tire-force reduction. Under certain conditions of tire pressure, velocity, and water depth, the smooth-treaded tires stop rotating and begin to plane even without the application of brakes. Results regarding the smooth-tire friction coefficients, friction coefficients of the diamond-treaded tire, effect o… more
Date: September 1958
Creator: Harrin, Eziaslav N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Mach 4 rocket-powered supersonic tunnel using ammonia-oxygen as working fluid

Description: From Summary: "A rocket-powered supersonic tunnel has been constructed to simulate the high heating rates encountered in hypersonic flow. A gas temperature of 4500 degrees Rankine at Mach 4 has been produced in the 15-inch test section of the tunnel. The calibration pressure data indicate reproducibility of test conditions in this facility. Physical, transport, and one-dimensional aerodynamic data from combustion products of ammonia and oxygen are included."
Date: September 1958
Creator: Graham, Robert W.; Guentert, Eleanor Costilow & Huff, Vearl N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Mass Transfer Cooling Near the Stagnation Point

Description: "A simplified analysis is made of mass transfer cooling - that is, injection of a foreign gas - near the stagnation point for two-dimensional and axisymmetric bodies. The reduction in heat transfer is given in terms of the properties of the coolant gas and it is shown that the heat transfer may be reduced considerably by the introduction of a gas having appropriate thermal and diffusive properties. The mechanism by which heat transfer is reduced is discussed" (p. 1).
Date: September 1958
Creator: Roberts, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Simplified T-Tail Oscillating in Yaw About the Fin Midchord

Description: Report presenting some experimental measurements of aerodynamic forces and moments on a simple T-tail configuration oscillating in yaw about an axis through the midchord of the vertical fin. Coefficients regarding the rolling moment of the horizontal stabilizer, rolling moment, yawing moment, and side force of the tail are provided.
Date: September 1958
Creator: Clevenson, Sherman A. & Leadbetter, Sumner A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of ground-reaction forces and vertical center-of-gravity accelerations of a bomber airplane taxiing over obstacles

Description: Report presenting an investigation made on an unswept-wing four-engine bomber airplane to determine the vertical and drag ground-reaction forces imposed on the landing gear when taxiing over obstacles of various sizes. Results are presented of the effects of ground speed and the widths and heights of the obstacles on the vertical and drag forces, vertical acceleration at the center of gravity of the airplane, on shock-strut displacement, and on response of the upper mass of the airplane structu… more
Date: September 1958
Creator: McKay, James M.; Sawyer, Richard H. & Hall, Albert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of the Motions of a Large Swept-Wing Airplane in Rough Air

Description: Note presenting flight test measurements of the angular and linear motions of a large swept-wing airplane in rough air for a range of altitudes. The measurements are summarized in the form of power spectra, root-mean-square values, and probability distributions. A procedure is given for extrapolating the measurements of the probability distributions and the power spectra to other turbulence conditions.
Date: September 1958
Creator: Rhyne, Richard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Method for Determining the Need to Rework or Replace Compressor Rotor Blades Damaged by Foreign Objects

Description: Note presenting a method for deciding whether jet-engine compressor blades that have been nicked in service are safe from fatigue failure with continued engine operation. The method involves determining the vibratory stress distribution of the blades with damage inflicted in the laboratory. The method is judged to be a realistic criterion on inspecting damaged blades.
Date: September 1958
Creator: Kaufman, Albert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Natural convection inside a flat rotating container

Description: Report presenting an exploration of Froude number, which is found to be the parameter that determines the effect of body rotations on internal natural convection flows. Explicit forms of Froude number are determined for the cases of predominant rotation and predominant axial force. Results indicated that in a heated cylindrical container no significant convective effects are generated by rotations alone.
Date: September 1958
Creator: Ostrach, Simon & Braun, Willis H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A nonlinear theory for predicting the effects of unsteady laminar, turbulent, or transitional boundary layers on the attenuation of shock waves in a shock tube with experimental comparison

Description: Report presenting a modification of the linearized attenuation theory by using an unsteady compressible local skin-friction coefficient, a nonlinear approach, and the consideration of transition effects. Curves for predicting attenuation for shock pressure ratios up to 20 and a range of shock-tube Reynolds numbers are provided.
Date: September 1958
Creator: Trimpi, Robert L. & Cohen, Nathaniel B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On Fully Developed Channel Flows: Some Solutions and Limitations, and Effects of Compressibility, Variable Properties, and Body Forces

Description: Note presenting an examination of the effects of compressibility, variable properties, and body forces on fully developed laminar flows, which indicated several limitations on such streams. In the absence of a pressure gradient, but in the presence of a body force, an exact fully developed gas flow results.
Date: September 1958
Creator: Maslen, Stephen H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On Possible Similarity Solutions for Three-Dimensional Incompressible Laminar Boundary-Layer Flows Over Developable Surfaces and with Proportional Mainstream Velocity Components

Description: Analysis is presented on the possible similarity solutions of the three-dimensional, laminar, incompressible, boundary-layer equations referred to orthogonal, curvilinear coordinate systems. Requirements of the existence of similarity solutions are obtained for the following: flow over developable surface and flow over non-developable surfaces with proportional mainstream velocity components.
Date: September 1958
Creator: Hansen, Arthur G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas

Description: The equations of shells are taken in the form of the general technical theory of shallow shells and shells of medium length. The aerodynamic forces acting on a shell are taken into account only as forces of excess pressure according to the formula proposed by A.A. Iliushin in reference 3.
Date: September 1958
Creator: Stepanov, R. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ordinates and theoretical pressure-distribution data for NACA 6- and 6A-series airfoil sections with thicknesses from 2 to 21 and from 2 to 15 percent chord, respectively

Description: Basic thickness forms for six different airfoil sections are tabulated for four different thicknesses of chord. Theoretical values of pressure and velocity ratios required to obtain theoretical airfoil pressure distributions are also provided.
Date: September 1958
Creator: Patterson, Elizabeth W. & Braslow, Albert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A phenomenological theory for the transient creep of metals at elevated temperatures

Description: Report presenting a modification of a theory for the behavior of metals at elevated temperatures to yield transient creep curves by assuming that the metal consists of two phases, each with its own elasticity and viscosity. The comparison between theoretical curves obtained with experimental data on pure aluminum, gamma iron, lead, and 7075-T6 aluminum alloy shows that the theory is adequate to account for the shape and position of the experimental curves.
Date: September 1958
Creator: Stowell, Elbridge Z.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary heat-transfer studies on two bodies of revolution at angle of attack at a Mach number of 3.12

Description: Report presenting local rates of heat transfer obtained for a cone-cylinder model and a parabolic-nosed-cylinder model at Mach number 3.12 and a range of angles of attack. For similar type boundary layers, heat-transfer coefficients at angle of attack were always higher than those at zero angle of attack at corresponding geometric locations.
Date: September 1958
Creator: Sands, Norman & Jack, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Procedure for calculating flutter at high supersonic speed including camber deflections, and comparison with experimental results

Description: Report presenting a method that can be used at high supersonic Mach numbers for calculating the flutter speed of wings with camber in their deflection modes. It is used to calculate the flutter speed of some wings that had been tested at Mach numbers of 1.3 and 3.0. Theoretical comparisons of the tested wings are also provided.
Date: September 1958
Creator: Morgan, Homer G.; Huckel, Vera & Runyan, Harry L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Propellant vaporization as a criterion for rocket-engine design; Calculations of chamber length to vaporize various propellants

Description: From Summary: "Vaporization rates were calculated for drops of n-heptane, ammonia, hydrazine, oxygen, and fluorine. The percent propellant vaporized is correlated with an effective chamber length for various spray conditions, and various engine-design and operating parameters. The results show that the effective chamber length required to vaporize a given high percentage of propellant is the shortest with oxygen and increases for fluorine, heptane, ammonia, and hydrazine in that order."
Date: September 1958
Creator: Priem, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The rate of fatigue-crack propagation in two aluminum alloys

Description: From Summary: "A general method has been developed for determination of fatigue-crack propagation rates. In order to provide a check on the theoretical predictions and to evaluate certain empirical constants appearing in the expression for the rate of fatigue-crack propagation, an extensive series of tests has been conducted. Sheet specimens, 2 inches and 12 inches wide, of 2024-T3 and 7075-T6 aluminum alloys were tested in repeated tension with constant-amplitude loading."
Date: September 1958
Creator: McEvily, Arthur J., Jr. & Illg, Walter
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Rate of reaction of gaseous fluorine with water vapor at 35 degrees C

Description: Report presenting testing of fluorine and water vapor, which react extremely slowly or not at all in the gas phase at 35 degrees Celsius at partial pressures of the reactants up to 40 mm of mercury. Results regarding the gross nature of the reaction, order of the reaction, kinetics of surface and gas-phase reactions, relative importance of surface and gas-phase reactions, and rate of surface reaction are provided.
Date: September 1958
Creator: Slabey, Vernon A. & Fletcher, Edward A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Relationship of Metal Surfaces to Heat-Aging Properties of Adhesive Bonds

Description: A study of the probable causes of deterioration of each of several adhesives in bonds to stainless steel at temperatures from 400 degrees to 550 degrees Fahrenheit. Preliminary studies of aluminum surfaces on which ions of metal used in stainless steel were introduced showed that iron was probably catalyzing a thermal deterioration of the adhesive. Results regarding the studies of adhesive bonds to aluminum surfaces and studies of adhesive bonds to stainless-steel surfaces are provided.
Date: September 1958
Creator: Black, J. M. & Blomquist, R. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Relative Motion in the Terminal Phase of Interception of a Satellite or a Ballistic Missile

Description: Note presenting the use of pilotless aircraft in the destructive interception of satellites and ballistic missiles, which has not been explored much due to the high speed and shift of emphasis due to forces. The main focus in this paper is on the terminal phase of the interceptor's flight.
Date: September 1958
Creator: Hord, Richard A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Second-Order Slender-Body Theory: Axisymmetric Flow

Description: "Slender-body theory for subsonic and supersonic flow past bodies of revolution is extended to a second approximation. Methods are developed for handling the difficulties that arise at round ends. Comparison is made with experiment and with other theories for several simple shapes" (p. 1).
Date: September 1958
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Similar Solutions for the Compressible Boundary Layer on a Yawed Cylinder With Transpiration Cooling

Description: Note presenting heat-transfer and skin-friction parameters obtained from exact numerical solutions to the laminar compressible-boundary-layer equations for the infinite cylinder in yaw. The results indicate that compressibility effects become important at large Mach numbers and yaw angles, with larger percentage effects on the skin friction than on heat transfer.
Date: September 1958
Creator: Beckwith, Ivan E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5

Description: Report presenting a simplified method that has been devised for the determination of the critical height of three-dimensional roughness particles required to promote premature transition of a laminar boundary layer on models of airplanes or airplane components. Results regarding the calculation of critical roughness height, minimization of roughness drag, limitations, and simplifying considerations are provided.
Date: September 1958
Creator: Braslow, Albert L. & Knox, Eugene C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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