UNT Libraries Government Documents Department - 222 Matching Results

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The Effect of Ice Formations on Propeller Performance

Description: "Measurements of propeller efficiency loss due to ice formation are supplemented by an analysis to establish the magnitude of efficiency losses to be anticipated during flight in icing conditions. The measurements were made during flight in natural icing conditions; whereas the analysis consisted of an investigation of changes in blade-section aerodynamic characteristics caused by ice formation and the resulting propeller efficiency changes. Agreement in the order of magnitude of efficiency los… more
Date: October 1950
Creator: Neel, Carr B., Jr. & Bright, Loren G.
Item Type: Refine your search to only Report
open access

Improvements in Heat Transfer for Anti-Icing of Gas-Heated Airfoils with Internal Fins and Partitions

Description: "The effect of modifying the gas passage of hollow metal airfoils by the addition of internal fins and partitions was experimentally investigated and comparisons were made among a basic unfinned airfoil section and two airfoil designs having metal fins attached at the leading edge of the internal gas passage. An analysis considering the effects of heat conduction in the airfoil metal was made to determine the internal modification effectiveness that may be obtained in gas-heated components, suc… more
Date: July 1950
Creator: Gray, Vernon H.
Item Type: Refine your search to only Report
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Penetration of Air Jets Issuing from Circular, Square, and Elliptical Orifices Directed Perpendicularly to an Air Stream

Description: From Summary: "An experimental investigation was conducted to determine the penetration of air jets directed perpendicularly to an air stream. Jets issuing from circular, square, and elliptical orifices were investigated and the jet penetration at a position downstream of the orifice was determined- as a function of jet density, jet velocity, air-stream density, air-stream velocity, effective jet diameter, and orifice flow coeffIcient. The jet penetrations were determined for nearly constant va… more
Date: February 1950
Creator: Ruggeri, Robert S.; Callaghan, Edmund E. & Bowden, Dean T.
Item Type: Refine your search to only Report
open access

Statistical Explanation of Spontaneous Freezing of Water Droplets

Description: Note presenting a statistical theory based on the presence of small crystallization nuclei suspended in water developed to explain experimental results showing that, on average, small droplets can be supercooled to lower temperatures than large ones. The average behavior of supercooled droplets is reproduced on the basis of probability theory with an assumed distribution of crystallization nuclei with respect to the temperatures at which the nuclei cause freezing.
Date: December 1950
Creator: Levine, Joseph
Item Type: Refine your search to only Report
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Photomicrographic Investigation of Spontaneous Freezing Temperatures of Supercooled Water Droplets

Description: "A photomicrographic technique for investigating seupercooled water droplets has been devised and. used. to determine the spontaneous freezing temperatures of seupercooled water droplets of the size ordinarily found. in the atmosphere. The freezing temperatures of 4527 droplets ranging from 8.75 to 1000 microns in diameter supported on a platinum surface and 571 droplets supported on copper were obtained. The average spontaneous freezing temperature decreased with decrease in the size of the dr… more
Date: July 1950
Creator: Dorsch, Robert G. & Hacker, Paul T.
Item Type: Refine your search to only Report
open access

Further Experimental Studies of Area Suction for the Control of the Laminar Boundary Layer on a Porous Bronze NACA 64A010 Airfoil

Description: Note presenting a low-turbulence wind-tunnel investigation of an NACA 64A010 airfoil with a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of area suction. This report primarily deals with additional tests of the same airfoil model equipped with a porous skin of lower porosity.
Date: May 1950
Creator: Braslow, Albert L. & Visconti, Fioravante
Item Type: Refine your search to only Report
open access

The Spanwise Distribution of Lift for Minimum Induced Drag of Wings Having a Given Lift and a Given Bending Moment

Description: "The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. The theory is limited to lifting surfaces traveling at subsonic speeds. It is found that the required shape of the downwash distribution can be obtained in an elementary way which is applicable to a variety of such problems" (p. 1).
Date: December 1950
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
open access

Effect of heat and power extraction on turbojet-engine performance 1: analytical method of performance evaluation with compressor-outlet air bleed

Description: Report presenting an analytical investigation of the performance of a turbojet engine with air bled off at the compressor outlet. A wide range of engine and flight conditions are covered and air bleeds of 0 to 15 percent of the air mass flow are considered. Results are provided in the form of generalized performance charts that are applicable to a wide range of operating conditions.
Date: March 1950
Creator: Hensley, Reece V.; Rom, Frank E. & Koutz, Stanley L.
Item Type: Refine your search to only Report
open access

Stress and distortion measurements in a 45 degree swept box beam subjected to antisymmetrical bending and torsion

Description: Report presenting an untapered aluminum-alloy box beam representing the main structural component of a full-span, two-spar, 45 degree swept wing with a carry-through section subjected to antisymmetrical tip bending and twisting loads such that stresses were kept below the proportional limit. Results regarding stresses due to antisymmetrical bending, stresses due to antisymmetrical torsion, distortions due to antisymmetrical bending, and distortions due to antisymmetrical torsion are provided.
Date: April 1950
Creator: Zender, George W. & Heldenfels, Richard R.
Item Type: Refine your search to only Report
open access

Tables of wing-aileron coefficients of oscillating air forces for two-dimensional supersonic flow

Description: Report presenting the wing-aileron coefficients of oscillating air forces for two-dimensional supersonic flow for a variety of Mach numbers. Various ratios of control-surface chord to airfoil chord are employed in the calculation and for each combination of chord ratio and Mach number, approximate 35 values of reduced frequency are utilized.
Date: March 1950
Creator: Huckel, Vera & Durling, Barbara J.
Item Type: Refine your search to only Report
open access

Velocity Distribution on Wing Sections of Arbitrary Shape in Compressible Potential Flow 3: Circulatory Flows Obeying the Simplified Density-Speed Relation

Description: "The method of computing velocity and pressure distributions along wing profiles under the assumption of the simplified density-speed relation, outlined in NACA Technical Note 1006, is extended to the case of a nonsymmetrical profile and a flow with circulation. The shape of the profile, the speed of the undisturbed flow, and a parameter determining the angle of attack may be prescribed. The problem is reduced to a nonlinear integral equation which can be solved numerically by an iteration meth… more
Date: March 1950
Creator: Bers, Lipman
Item Type: Refine your search to only Report
open access

A method of computing subsonic flows around given airfoils

Description: From Summary: "An extremely simple computational method is established for obtaining circulatory flows around given bodies to a high degree of accuracy for flows satisfying the linear pressure and specific-volume equation of state. The method depends not on an integral equation but on the transformation from the holograph to the physical plane involving the determination of an arbitrary analytic function. The determination of the arbitrary analytic function by elementary means results in a clos… more
Date: March 1950
Creator: Gelbart, Abe & Resch, Daniel
Item Type: Refine your search to only Report
open access

On the Continuation of a Potential Gas Flow Across the Sonic Line

Description: "Simple, sufficient conditions are given under which a two-dimensional steady compressible flow can be continued across the line of Mach number 1 as a continuous supersonic flow. Methods for the actual computation of the flow are described. The problem is of importance in the theory of transonic flows past airfoils" (p. 1).
Date: April 1950
Creator: Bers, Lipman
Item Type: Refine your search to only Report
open access

Method of Experimentally Determining Radial Distributions of Velocity Through Axial-Flow Compressor

Description: Note presenting a method by which the energy and continuity relations are simultaneously solved to express the velocity distributions downstream of any compressor blade row in terms of outlet total temperature, total pressure, and relative flow angle. The method is intended for use in units in which only a limited amount of experimental data can be obtained.
Date: April 1950
Creator: Finger, Harold B.
Item Type: Refine your search to only Report
open access

The effect of rate of change of angle of attack on the maximum lift of a small model

Description: Report presenting a wind-tunnel investigation of a partial model of a conventional fighter airplane to determine the effects of rate of change of angle of attack on its maximum lift. The results indicated that the maximum lift coefficient increased linearly with pitching velocity up to a limit value of the lift coefficient which depended on the Mach number.
Date: March 1950
Creator: Harper, Paul W. & Flanigan, Roy E.
Item Type: Refine your search to only Report
open access

Dynamic Similitude Between a Model and a Full-Scale Body for Model Investigation at Full-Scale Mach Number

Description: Note presenting an analysis for interpreting results of dynamic tests of a model investigated at full-scale Mach number in terms of the corresponding full-scale body. The analysis indicates that dynamic similarity for such a condition can be closely approximated although the effect of gravity is not to scale.
Date: March 1950
Creator: Neihouse, Anshal I. & Pepoon, Philip W.
Item Type: Refine your search to only Report
open access

On the Particular Integrals of the Prandtl-Busemann Iteration Equations for the Flow of a Compressible Fluid

Description: Note presenting the particular integrals of the second-order and third-order Prandtl-Busemann iteration equations for the flow of a compressible fluid that have been obtained by means of the method in which the complex conjugate variables are utilized as the independent variables of the analysis. The forms of the particular integrals, derived for subsonic flow, are readily adapted to supersonic flows with only a change in sign of one of the parameters of the problem.
Date: August 1950
Creator: Kaplan, Carl
Item Type: Refine your search to only Report
open access

Relation Between Inflammables and Ignition Sources in Aircraft Environments

Description: From Summary: "A literature survey was conducted to determine the relation between aircraft ignition sources and inflammables. Available literature applicable to the problem of aircraft fire hazards is analyzed and discussed herein. Data pertaining to the effect of many variables on ignition temperatures, minimum ignition pressures, and minimum spark-ignition energies of inflammables, quenching distances of electrode configurations, and size of openings incapable of flame propagation are presen… more
Date: December 1950
Creator: Scull, Wilfred E.
Item Type: Refine your search to only Report
open access

A General Integral Form of the Boundary-Layer Equation for Incompressible Flow With an Application to the Calculation of the Separation Point of Turbulent Boundary Layers

Description: Note presenting a general integral form of the boundary-layer equation that is derived from the Prandtl partial-differential boundary-layer equation. The general integral equation, valid for either laminar or turbulent incompressible boundary-layer flow, contains the Von Karman momentum equation, the kinetic-energy equation, and the Loitsianskii equation as special cases.
Date: August 1950
Creator: Tetervin, Neal & Lin, Chia Chiao
Item Type: Refine your search to only Report
open access

Pressure Distribution and Damping in Steady Pitch at Supersonic Mach Numbers of Flat Swept-Back Wings Having All Edges Subsonic

Description: Note presenting a method for calculating the pressure distribution and damping in steady pitch at supersonic Mach numbers of thin, flat, sweptback wings with all edges straight and subsonic. The two steps of the method are described and applied to wings with streamwise tips. The analysis showed that abrupt changes in pressure should occur along the various primary and reflected Mach lines on the wing, especially those originating at the tips of the leading edge.
Date: October 1950
Creator: Walker, Harold J. & Ballantyne, Mary B.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at Low Speed of the Lateral Control Characteristics of an Unswept Untapered Semi-Span Wing of Aspect Ratio 3.13 Equipped With Various 25-Percent-Chord Plain Ailerons

Description: Report presenting a wind-tunnel investigation at low speed to determine the lateral control characteristics of an unswept untapered semispan wing of aspect ratio 3.13 equipped with 25-percent-chord plain unsealed ailerons with various spans and spanwise locations. Results regarding wing aerodynamic characteristics and aileron control characteristics are provided.
Date: October 1950
Creator: Johnson, Harold S. & Hagerman, John R.
Item Type: Refine your search to only Report
open access

Effect of heat and power extraction on turbojet-engine performance 3: analytical determination of effects of shaft-power extraction

Description: Report presenting an analysis of the performance of an axial-flow-type turbojet engine operating with shaft-power extraction by matching experimentally determined component characteristics of a typical axial-flow engine. General working charts are provided to investigate engine performance with variable and rated tail-pipe-nozzle area operation at constant turbine-inlet temperature, engine speed, and thrust.
Date: October 1950
Creator: Koutz, Stanley L.; Hensley, Reece V. & Rom, Frank E.
Item Type: Refine your search to only Report
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