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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15391 - 15440 of 19,853
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Wind-tunnel vibration tests of dual-rotating propellers
No Description digital.library.unt.edu/ark:/67531/metadc62121/
Flight measurements of the effect of various amounts of aileron droop on the low-speed lateral-control characteristics of an observation airplane
No Description digital.library.unt.edu/ark:/67531/metadc279604/
Elimination of rumble from the cooling ducts of a single-engine pursuit airplane
No Description digital.library.unt.edu/ark:/67531/metadc61231/
Analysis of Oil Production in the Near-Depleted Mexia-Powell Fault-Line Fields of Texas
Report issued by the U.S. Bureau of Mines on the oil fields located near the Mexia-Powell fault line in Texas. Properties of the oil fields, including geology and oil production, are presented. This report includes tables, graphs, maps, and illustrations. digital.library.unt.edu/ark:/67531/metadc38413/
Antiknock effectiveness of xylidines in small-scale engines
No Description digital.library.unt.edu/ark:/67531/metadc62346/
Bearing strengths of some wrought-aluminum alloys
Although a number of investigations of the bearing strength of aluminum alloys have been made, the problem remains one of considerable interest to the aircraft industry. For this reason it has seemed advisable to make additional tests of the commonly used aircraft alloys in an effort to establish a better basis for the selection of allowable bearing values. Current design practice does not recognize the effect of edge distance upon bearing strengths, and for this reason edge distance was one of the principal variables considered in this investigation. The increasing emphasis being placed upon permanent set limitations makes it essential that more information on bearing yield phenomena be obtained. The object of this investigation was to determine bearing yield and ultimate strengths of the following aluminum alloy products: 17S-T, 24S-T, Alclad 24S-T, 24S-RT, 52S-0, 52S-1/2H, 52S-H, 53S-T, and 61S-T extrusions. Ratios of these bearing properties to tensile properties were also determined. digital.library.unt.edu/ark:/67531/metadc54692/
Byproduct Coke-Oven Tests of Washington Coals
Report issued by the U.S. Bureau of Mines on the coking-coal testing done on Washington coal. Descriptions of the testing, and properties of the coals tested are presented. This report includes tables, and photographs. digital.library.unt.edu/ark:/67531/metadc38415/
Determination of the damping moment in yawing for tapered wings with partial-span flaps
No Description digital.library.unt.edu/ark:/67531/metadc61258/
Development of thermal ice-prevention equipment for the B-17F airplane
No Description digital.library.unt.edu/ark:/67531/metadc61807/
Economic Considerations in the Recovery of Magnesia from Dolomite
Report issued by the U.S. Bureau of Mines discussing the recovery of magnesia from dolomite. Processes and methods of recovery are described. This report includes tables. digital.library.unt.edu/ark:/67531/metadc67025/
The Effect of Artificial Aging on the Tensile Properties of Alclad 24S-T and 24S-T Aluminum Alloy
An experimental study was made to determine the effect of artificial aging on the tensile properties of alclad 24S-T and 24S-T aluminum-alloy sheet material. The results of the tests show that certain combinations of aging time and temperature cause a marked increase in the yield strength and a small increase in the ultimate strength; these increases are accompanied by a very large decrease in elongation. A curve is presented that shows the maximum yield strengths that can be obtained by aging this material at various combinations of time and temperature. The higher values of yield stress are obtained in material aged at relatively longer times and lower temperatures. digital.library.unt.edu/ark:/67531/metadc62249/
The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel
The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing movements of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained. The tests showed the following effects of increased rolling and yawing moments of inertia: no appreciable change in spiral stability; reductions in oscillatory stability that were serious at high values of dihedral; a reduction in the sensitivity of the model to gust disturbances; and a reduction in rolling acceleration provided by the ailerons, which caused a marked increase in time to reach a given angle of bank. The general flight behavior of the model became worse with increasing moments of inertia but, with combinations of small effective dihedral and large vertical-tail area, satisfactory flight characteristics were obtained at all moment-of-inertia conditions. digital.library.unt.edu/ark:/67531/metadc60939/
The effect of xylidines on the load-carrying capacity of an aircraft-engine oil I
No Description digital.library.unt.edu/ark:/67531/metadc62342/
The effect of xylidines on the stability of an aircraft-engine lubricating oil
No Description digital.library.unt.edu/ark:/67531/metadc62344/
Engineering Study of the Rodessa Oil Field in Louisiana, Texas, and Arkansas
Report issued by the Bureau of Mines over drilling operations in Texas, Arkansas, and Louisiana. Results of the operations are discussed. This report includes maps, tables, illustrations, and photographs. digital.library.unt.edu/ark:/67531/metadc38414/
Flutter tests of modified SB2U model in 16-foot tunnel
No Description digital.library.unt.edu/ark:/67531/metadc60879/
De-icing of an aircraft-engine induction system
No Description digital.library.unt.edu/ark:/67531/metadc61806/
Improved baffle designs for air-cooled engine cylinders
No Description digital.library.unt.edu/ark:/67531/metadc61903/
An investigation of aircraft heaters XII : performance of a formed-plate crossflow exhaust gas and air heat exchanger
No Description digital.library.unt.edu/ark:/67531/metadc62695/
An investigation of aircraft heaters XIII : performance of corrugated and noncorrugated fluted type exhaust gas-air heat exchangers
No Description digital.library.unt.edu/ark:/67531/metadc61694/
A method for determining the column curve from tests of columns with equal restraints against rotation on the ends
The results are presented of a theoretical study for the determination of the column curve from tests of column specimens having ends equally restrained against rotation. The theory of this problem is studied and a curve is shown relating the fixity coefficient c to the critical load, the length of the column, and the magnitude of the elastic restraint. A method of using this curve for the determination of the column curve for columns with pin ends from tests of columns with elastically restrained ends is presented. The results of the method as applied to a series of tests on thin-strip columns of stainless steel are also given. digital.library.unt.edu/ark:/67531/metadc54706/
A method of estimating the knock rating of hydrocarbon fuel blends
No Description digital.library.unt.edu/ark:/67531/metadc62267/
Preliminary vibration and flutter studies on P-47 tail
No Description digital.library.unt.edu/ark:/67531/metadc61591/
Summary report on the induction of water to the inlet air as a means of internal cooling in aircraft-engine cylinders
No Description digital.library.unt.edu/ark:/67531/metadc61971/
Survey of Subsurface Brine-Disposal Systems in Western Kansas Oil Fields
Report issued by the U.S. Bureau of Mines on the disposal of brine from oil field injections. Information on handling and disposing of brine and injection equipment is presented. This report includes tables, and a map. digital.library.unt.edu/ark:/67531/metadc38416/
Wind-tunnel investigation of a full-span retractable flap in combination with full-span plain and internally balanced ailerons on a tapered wing
No Description digital.library.unt.edu/ark:/67531/metadc61420/
Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61629/
Description of stress-strain curves by three parameters
A simple formula is suggested for describing the stress-strain curve in terms of three parameters; namely, Young's modulus and two secant yield strengths. Dimensionless charts are derived from this formula for determining the stress-strain curve, the tangent modulus, and the reduced modulus of a material for which these three parameters are given. Comparison with the tensile and compressive data on aluminum-alloy, stainless-steel, and carbon-steel sheet in NACA Technical Note No. 840 indicates that the formula is adequate for most of these materials. The formula does not describe the behavior of alclad sheet, which shows a marked change in slope at low stress. It seems probable that more than three parameters will be necessary to represent such stress-strain curves adequately. digital.library.unt.edu/ark:/67531/metadc54697/
Design, selection, and installation of aircraft heat exchangers
No Description digital.library.unt.edu/ark:/67531/metadc61934/
Determination of general relations for the behavior of turbulent boundary layers
No Description digital.library.unt.edu/ark:/67531/metadc279609/
Effect of rivet pitch upon the fatigue strength of single-row riveted joints of 0.025- to 0.025-inch 24S-T alclad
S-N curves at the range ratio of 0.2 were experimentally obtained for each of the following values of rivet pitch P as used in a single-row lap joint of 0.025- to 0.025-inch 24S-T alclad with one-eight AN430 round-head rivets: p=0.5, 0.75, 1.0, 1.5. Families of constant rivet pitch curves, which define the fatigue life for specimens studied, were developed. Curves showing the variation of the effective stress concentration factor in fatigue with rivet pitch and maximum load per rivet were also established. digital.library.unt.edu/ark:/67531/metadc54686/
Effect of turbulence on air-flow measurements behind orifice plates
No Description digital.library.unt.edu/ark:/67531/metadc62563/
The effect of xylidines on the corrosiveness of aircraft-engine oil
No Description digital.library.unt.edu/ark:/67531/metadc62341/
Flight measurements of compressibility effects on a three-blade thin Clark Y propeller operating at constant advance-diameter ratio and blade angle
No Description digital.library.unt.edu/ark:/67531/metadc62161/
Investigation for the development of a high-speed antiaircraft tow target
No Description digital.library.unt.edu/ark:/67531/metadc62437/
Investigation of methods of reducing the temperature variation among cylinders on air-cooled aircraft engines
No Description digital.library.unt.edu/ark:/67531/metadc61980/
Knocking tendency of an air-cooled aircraft-engine cylinder with one and with two spark plugs
No Description digital.library.unt.edu/ark:/67531/metadc62045/
Measurements of friction coefficients in a pipe for subsonic and supersonic flow of air
No Description digital.library.unt.edu/ark:/67531/metadc62675/
NACA Mach number indicator for use in high-speed tunnels
No Description digital.library.unt.edu/ark:/67531/metadc279639/
NACA procedure for flight tests of aileron characteristics of airplanes
No Description digital.library.unt.edu/ark:/67531/metadc61631/
On a function-theory method for obtaining potential-flow patterns of a compressible fluid
No Description digital.library.unt.edu/ark:/67531/metadc62604/
Porpoising: a comparison of theory with experiment
No Description digital.library.unt.edu/ark:/67531/metadc60896/
Relation of preignition and knock to allowable engine temperatures
No Description digital.library.unt.edu/ark:/67531/metadc61862/
Round heat-treated chromium-molybdenum-steel tubing under combined loads
The results of tests of round heat-treated chromium-molybdenum-steel tubing are presented. Tests were made on tubing under axial load, bending load, torsional load, combined bending and axial load, combined bending and torsional load, and combined axial, bending, and torsional load. Tensile and compressive tests were made to determine the properties of the material. Formulas are given for the evaluation of the maximum strength of this steel tubing under individual or combined loads. The solution of an example is included to show the procedure to be followed in designing a tubular cantilever member to carry combined loads. digital.library.unt.edu/ark:/67531/metadc54673/
Selection of oil coolers to avoid congealing
No Description digital.library.unt.edu/ark:/67531/metadc62025/
Some yawing tests of a 1/30-scale model of the hull of the XPB2M-1 flying boat
No Description digital.library.unt.edu/ark:/67531/metadc62669/
Theory of self-excited mechanical oscillations of hinged rotor blades
No Description digital.library.unt.edu/ark:/67531/metadc62585/
Water tolerance of aviation gasoline containing xylidines
No Description digital.library.unt.edu/ark:/67531/metadc62340/
Wind-tunnel investigation of control-surface characteristics XIII : various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61537/
Wind-tunnel tests of four full-scale seaplane floats
No Description digital.library.unt.edu/ark:/67531/metadc61713/