UNT Libraries Government Documents Department - 193 Matching Results

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Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Description: From Introduction: "The fundamental integral equation for the pressure distribution on an oscillating thin airfoil moving at subsonic speed has been derived by Possio in reference 1. Collocation procedures have been used by Possio, Frazer, and Skan, and others to obtain lift and moment on an oscillating first plate. An important contribution has been made by Dietze (see reference 2 and 3), who has developed an iterative procedure for numerical solution of Possio's integral equation."
Date: October 1950
Creator: Turner, M. J. & Rabinowitz, S.
open access

An air-flow-direction pickup suitable for telemetering use on pilotless aircraft

Description: From Summary: "A free-swiveling vane-type pickup for measuring air flow direction in both the angle-of-attack and angle-of-sideslip directions is described. Test results are presented which indicate that the pickup is aerodynamically stable and has an accuracy, obtained from a bench calibration, of better than 0.3^o under conditions including acceleration up to 20g in any direction, Mach numbers from 0.5 to 2.8, dynamic pressures up to at least 65 psi. Equations and curves which can be used to … more
Date: October 1956
Creator: Ikard, Wallace L.
open access

Amplitude of Supersonic Diffuser Flow Pulsations

Description: From Introduction: "This report, prepared at the NACA Lewis laboratory, presents a theoretical evaluation of the variables which govern pulsation amplitude for the cold-flow engine."
Date: October 1955
Creator: Sterbentz, William H. & Davids, Joseph
open access

Analogy Between Mass and Heat Transfer with Turbulent Flow

Description: From Introduction: "The purpose of this paper is to present an analysis of the mass- and heat-transfer process in terms of a simplified physical picture of the turbulent boundary layer subject to the assumptions previously described."
Date: October 1953
Creator: Callaghan, Edmund E.
open access

An analysis of acceleration, airspeed, and gust-velocity data from one type of four-engine transport airplane operated over two domestic routes

Description: From Introduction: "As part of a continuing study of the gust and load histories for transport airplanes (see, for example, refs. 1 and 2), samples of VGH records have been obtained from two four-engine commercial transport airplanes. The data samples represent 839 and 1,080 flight hours of operation on two transcontinental routes and cover operations up to an altitude of 25,000 feet."
Date: October 1955
Creator: Copp, Martin R. & Coleman, Thomas L.
open access

An analysis of airspeed, altitude, and acceleration data obtained from a twin-engine transport airplane operated over a feeder-line route in the Rocky Mountains

Description: "Time-history data of airspeed, altitude, and acceleration obtained with the NACA VGH recorder from a twin-engine airplane operated by a regional feeder airline in the Rocky Mountains are evaluated to determine the magnitude and frequency of occurrence of gusts and gust accelerations and the operating airspeeds and altitudes. The results obtained are compared with the results previously obtained from a representative short-haul and long-haul operation" (p. 1).
Date: October 1956
Creator: Copp, Martin R. & Fetner, Mary W.
open access

Analysis of shear strength of honeycomb cores for sandwich constructions

Description: From Introduction: "In the present report an analysis was undertaken to arrive at a mathematical formula by which the shear strengths of honeycomb core materials could be calculated. Experimental verification of the formula of the present paper was obtained by tests of honeycomb-type sheets of resin-impregated paper; two groups of specimens were tested, each of which represented a different resin-impregation treatment of the basic paper."
Date: October 1950
Creator: Werren, Fred & Norris, Charles Brazer
open access

An Analysis of the Effect of Several Parameters on the Stability of an Air-Lubricated Hydrostatic Thrust Bearing

Description: From Introduction: "The present investigation considers a simple nonrotating thrust bearing consisting of two round flat disks of finite diameter separated by a thin film of air. The nonlinear differential equations governing the motion of the bearing when disturbed were solved on a high-speed digital computing machine. In addition, these solutions provide a means for checking the validity of more simplified solutions (e.g., ref. 1)."
Date: October 1957
Creator: Roudebush, William H.
open access

An Analytic Determination of the Flow Behind a Symmetrical Curved Shock in a Uniform Stream

Description: From Introduction: "The present report is concerned with a closer investigation of the validity of this method and includes a more complete formulation, as well as the computation procedure, of the series expansion. As stated in reference 1, the flow thus determined depends only on the Mach number when the detached distance is adopted as the length scale. General formulas and the procedure of calculation are given in this report for such purposes."
Date: October 1951
Creator: Lin, C. C. & Shen, S. F.
open access

An approximate method of calculating pressures in the tip region of a rectangular wing of circular-arc section at supersonic speeds

Description: From Introduction: "The present paper introduces the approximate method by means of which it is possible to calculate the pressures in the tip region of a rectangular with a symmetrical circular-arc section to a higher degree of accuracy than is possible with the usual linear methods."
Date: October 1950
Creator: Czarnecki, K. R. & Mueller, James N.
open access

An Approximate Solution for Axially Symmetric Flow Over a Cone With an Attached Shock Wave

Description: "It is shown that the streamlines in an angular neighborhood of the surface of an unyawed circular cone with an attached shock wave are, to a first approximation, portions of hyperbolas. This fact is used as a basis for the development of an approximate solution in which the shock-wave orientation and the flow field behind the shock wave are given explicitly in terms of the free-stream Mach number, the vertex angle of the body cone, and the ratio of specific heats of the gas. The approximate so… more
Date: October 1955
Creator: Hord, Richard A.
open access

Averaging of Periodic Pressure Pulsations by a Total-Pressure Probe

Description: Note presenting information on the average pressure indicated by a total-pressure probe subjected to a stagnation pressure that alternates periodically between two constant values. Calculated and experimental data are in good agreement and errors are reduced when the probe design is such as to ensure laminar-flow pulsations in the probe at all times.
Date: October 1955
Creator: Johnson, R. C.
open access

Axial-load fatigue tests on notched and unnotched sheet specimens of 61S-T6 aluminum alloy, annealed 347 stainless steel, and heat-treated 403 stainless steel

Description: From Summary: "Axial-load fatigue tests at a stress ratio of zero were performed on notched and unnotched sheet specimens of 61S-T6 aluminum alloy and 347 and 403 stainless steels. Special emphasis was placed on tests at high stress levels which produce failures in small numbers of cycles."
Date: October 1953
Creator: Hardrath, Herbert F.; Landers, Charles B. & Utley, Elmer C., Jr.
open access

Band-Pass Shock and Vibration Absorbers for Application to Aircraft Landing Gear

Description: Note presenting a description of a new class of frequency-selective shock absorbers called band-pass shock absorbers, which were conceived as a means of overcoming some of the limitations of conventional shock absorbers. The shock absorbers may be designed to isolate two bodies from each other over certain ranges of exciting frequencies or rates of load application while coupling them over the remainder of the frequency spectrum.
Date: October 1956
Creator: Schnitzer, Emanuel
open access

Bending of Thin Plates With Compound Curvature

Description: Report presenting an analysis for the deformation of a doubly curved thin plate under edge loads or surface loads for small deflections. The method is particularly useful for a plate whose radius of curvature in one direction is large compared with its length and width dimensions.
Date: October 1952
Creator: Lew, H. G.
open access

Bonding of molybdenum disulfide to various materials to form a solid lubricating film 2: friction and endurance characteristics of films bonded by practical methods

Description: Report exploring the use of molybdenum disulfide as a solid-film lubricant, especially in applications where designs or higher temperatures preclude liquid lubricants, because of its good frictional and thermal properties. An investigation was conducted to determine practical methods of bonding MoS2 to materials to form solid-film lubricants and friction and endurance characteristics of films so formed.
Date: October 1952
Creator: Godfrey, Douglas & Bisson, Edmond E.
open access

Boundary-layer measurements in 3.84- by 10-inch supersonic channel

Description: Report presenting boundary-layer measurements in the transonic and supersonic regions of a channel with maximum cross-sectional dimensions 3.84 by 10 inches and designed by potential-flow methods for a uniform Mach number of 2.08. Results regarding the Mach number distribution along the channel, temperature recovery and Prandtl number, boundary layer development, skin-friction coefficient, and secondary flows are provided.
Date: October 1950
Creator: Brinich, Paul F.
open access

Burning Velocities of Various Premixed Turbulent Propane Flames on Open Burners

Description: Note presenting the measurement of turbulent burning velocities for premixed propane flames at room temperature and atmospheric pressure. The measurements were made for systems of various laminar burning velocities, densities, and viscosities. Experimental results and comparison with previous work are provided.
Date: October 1955
Creator: Wagner, Paul
open access

Calculated spanwise lift distributions and aerodynamic influence coefficients for swept wings in subsonic flow

Description: Report presenting spanwise lift distribution calculations for 61 swept wings with various aspect ratios and taper ratios and with a variety of angle-of-attack or twist distributions, including flap and aileron deflections, by means of the Weissinger method with eight control points on the semispan. Also calculated were the aerodynamic influence coefficients which pertain to a certain definite set of stations along the span.
Date: October 1955
Creator: Diederich, Franklin W. & Zlotnick, Martin
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