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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
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
open access

Measurement of the moments of inertia of an airplane by a simplified method

Description: Report presenting a simplified method for the experimental determination of the moments of inertia, product of inertia, and inclination of the principal axes, the associated equipment and techniques, and the application of this method to a conventional airplane.
Date: October 1950
Creator: Turner, Howard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Gust-tunnel investigation of a wing model with semichord line swept back 60 degrees

Description: Report presenting an investigation in the gust tunnel of a 60 degree sweptback-wing model to determine the effect of a large angle of sweep on gust loads. A simplified method of analysis, which uses a slope of the lift curve derived by the cosine law and which uses strip theory to estimate the penetration effect, appears to be applicable to the prediction of gust loads on wings swept as much as 60 degrees.
Date: October 1950
Creator: Pierce, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical supersonic characteristics of inboard trailing-edge flaps having arbitrary sweep and taper: Mach lines behind flap leading and trailing edges

Description: Report presenting generalized expressions for closed form by means of linearized theory for the aerodynamic characteristics due to the deflection of inboard trailing-edge flaps. The analysis considers the effects of Mach number and flap aspect ratio, taper ratio, and sweep for conditions where Mach lines lie behind the flap leading and trailing edges. Design charts are presented for rapid estimation of the aerodynamic characteristics due to flap deflection.
Date: October 1950
Creator: Kainer, Julian H. & Marte, Jack E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Graphical Method for Obtaining Flow Field in Two-Dimensional Supersonic Stream to Which Heat Is Added

Description: Report presenting a graphical method for obtaining the two-dimensional supersonic flow with moderate heat addition. The basic equations were derived for flows in which the total temperature has a continuous variation with displacement in the direction of the flow.
Date: November 1950
Creator: Pinkel, I. Irving & Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free Oscillations of an Atmosphere in Which Temperature Increases Linearly With Height

Description: Note presenting the concept that when the temperature in the atmosphere increases linearly with height, the speed of propagation of long waves does not approach a limit with increasing wave length, as in the case of an atmosphere in which the temperature at great heights is assumed to be constant or decreasing, but increases linearly with the period.
Date: October 1950
Creator: Pekeris, C. L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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