Technical Report Archive & Image Library (TRAIL) - 53 Matching Results

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Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 2: maximum thickness at midchord

Description: "The lift, drag, and pitching-moment characteristics of a triangular wing, having an aspect ratio of 2 and a symmetrical double-wedge profile of 5-percent-chord maximum thickness at midchord, have been evaluated from wind-tunnel tests at Mach numbers from 0.50 to 0.975 and from 1.09 to 1.49 and at Reynolds numbers ranging from 0.67 to 0.85 million. The lift, drag, and pitching-moment coefficients of the triangular wing with a leading-edge sweepback of approximately 63 degrees did not exhibit th… more
Date: December 3, 1948
Creator: Walker, Harold J. & Berggren, Robert E.
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 7, Pressure and Temperature Distributions

Description: Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow turbojet engine were investigated. Data are included for a range of simulated altitudes from 5000 to 45000 feet, Mach numbers from 0.24 to 1.08, and corrected engine speeds from 10,550 to 13,359 rpm.
Date: December 10, 1948
Creator: Saari, Martin J. & Prince, William R.
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of tail-pipe burning with a Westinghouse X24C-4B axial-flow turbojet engine

Description: From Summary: "Thrust augmentation of an axial-flow type turbojet engine by burning fuel in the tail pipe has been investigated in the NACA Cleveland altitude wind tunnel. The performance was determined over a range of simulated flight conditions and tail-pipe fuel flows. The engine tail pipe was modified for the investigation to reduce the gas velocity at the inlet of the tail-pipe combustion chamber and to provide an adequate seat for the flame; four such modifications were investigated."
Date: December 13, 1948
Creator: Fleming, William A. & Wallner, Lewis E.
Partner: UNT Libraries Government Documents Department
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An Analysis of Project Data on the Corrosion of Uranium in Various Media

Description: This is a summarizing and reviewing report in which almost all the experimental data representing Project work done prior to 1949 on the corrosion of pure uranium are brought together and analyzed. New data obtained in this laboratory on corrosion rates in laboratory atmosphere and on the identification of corrosion products by electron diffraction are included. The data for corrosion in each of several different media have been plotted according to logarithm-of-the-rate versus reciprocal-tempe… more
Date: December 22, 1948
Creator: Waber, James T. (James Thomas), 1920-
Partner: UNT Libraries Government Documents Department
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An analysis of the airspeeds and normal accelerations of Boeing B-247 and B-247D airplanes in commercial transport operation

Description: From Introduction: "The results of analyses of V-G data given in references 1 to 5 have shown that the flight loads of airplanes operated in commercial transport service are influenced by operating speeds and by forecasting and dispatching practices as reflected in differences between operations during the prewar and wartime periods. The available data are summarized and the flight results are compared with the results of analyses made in references 1 to 5."
Date: December 1948
Creator: Walker, Walter G. & Hadlock, Ivan K.
Partner: UNT Libraries Government Documents Department
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An analytical method of estimating turbine performance

Description: From Introduction: "An analytical method for estimating turbine performance from the blade angle8 and flow areas was therefore developed at the NACA Lewis laboratory and is described herein."
Date: December 29, 1948
Creator: Kochendorfer, Fred D. & Nettles, J. Cary
Partner: UNT Libraries Government Documents Department
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An analytical method of estimating turbine performance

Description: From Introduction: "An analytical method for estimating turbine performance from angles and flow areas was therefore developed at the NACA Lewis laboratory in 1947 and is described herein."
Date: December 29, 1948
Creator: Kochendorfer, Fred D. & Nettles, J. Cary
Partner: UNT Libraries Government Documents Department
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The application of Green's theorem to the solution of boundary-value problems in linearized supersonic wing theory

Description: From Introduction: "The present paper is restricted to a discussion of wing theory subject to the assumptions of linearized compressible flow. It therefore employs solutions of Laplace's equation and the wave equation for cases where the boundary condition are specified in the plane of the wing."
Date: December 22, 1948
Creator: Heaslet, Max A. & Lomax, Harvard
Partner: UNT Libraries Government Documents Department
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Calculated Performance of a Compression-Ignition Engine-Compressor-Turbine Combination Based on Experimental Data

Description: Note presenting calculations based on test data taken on a single-cylinder compression-ignition engine with a compression ratio of 13.1 and an engine speed of 2200 rpm to determine the performance at sea-level conditions of a compression-ignition engine geared together with a compressor and a turbine. The net specific power output increased with decreasing compression ratio and with increasing fuel-air ratio and engine speed.
Date: December 1948
Creator: Mendelson, Alexander
Partner: UNT Libraries Government Documents Department
open access

Calculation of the Aerodynamic Loading of Flexible Wings of Arbitrary Plan Form and Stiffness

Description: "A method is presented for calculating the aerodynamic loading, the divergence speed, and certain stability derivatives of wings and tail surfaces of arbitrary plan form and stiffness. Provision is made for using either stiffness curves and root-rotation constants or influence coefficients in the analysis. Computing forms, tables of numerical constants required in the analysis, and an illustrative example are included to facilitate calculations by means of the method" (p. 1).
Date: December 24, 1948
Creator: Diederich, Franklin W.
Partner: UNT Libraries Government Documents Department
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Calculation of the aerodynamic loading of swept and unswept flexible wings of arbitrary stiffness

Description: A method is presented for calculating the aerodynamic loading, the divergence speed, and certain stability derivatives of swept and unswept wings and tail surfaces of arbitrary stiffness. Provision is made for using either stiffness curves and root rotation constants or structural influence coefficients in the analysis. Computing forms, tables of numerical constants required in the analysis, and an illustrative example are included to facilitate calculations by means of the method.
Date: December 24, 1948
Creator: Diederich, Franklin W.
Partner: UNT Libraries Government Documents Department
open access

Charts for the conical part of the downwash field of swept wings at supersonic speeds

Description: Report presenting analytical expressions derived from the downwash throughout the entire induced flow field of lifting triangles of infinite chord with the leading edges forward or behind the Mach cone. Results regarding the downwash charts, variation of downwash distribution with leading-edge sweep angle, and additional factors affecting the downwash are provided.
Date: December 1948
Creator: Nielsen, Jack N. & Perkins, Edward W.
Partner: UNT Libraries Government Documents Department
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Comparison of National Bureau of Standards ceramic coatings L-7C and A-417 on turbine blades in a turbojet engine

Description: Report presenting an investigation to determine which of two ceramic coatings, L-7C and A-417, developed by the National Bureau of Standards is more suitable as a protective coating for turbine blades in a turbojet engine. Four cast Vitallium turbine blades, two coated with each of the ceramics, were installed in a turbine wheel of a turbojet engine and subjected to accelerated cyclic life tests.
Date: December 22, 1948
Creator: Morse, C. Robert
Partner: UNT Libraries Government Documents Department
open access

Comparison of Theoretical and Experimental Heat-Transfer Characteristics of Bodies of Revolution at Supersonic Speeds

Description: "An investigation of the three important factors that determine convective heat-transfer characteristics at supersonic speeds, location boundary-layer transition, recovery factor, and heat-transfer parameter has been performed at Mach numbers from 1.49 to 1.18. The bodies of revolution that were tested had, in most cases, laminar boundary layers, and the test results have been compared with available theory. Boundary-layer transition was found to be affected by heat transfer" (p. 1301).
Date: December 17, 1948
Creator: Scherrer, Richard
Partner: UNT Libraries Government Documents Department
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Control considerations for optimum power proportionment in turbine-propeller engines

Description: Report presenting an analysis of a turbine-propeller engine operating at constant speed in order to provide information regarding factors influencing optimum proportionment of power between propeller and jet, improvement in engine performance attainable from controlled proportionment of power, and control relations for optimum proportionment of power.
Date: December 1948
Creator: Heidmann, Marcus F. & Novik, David
Partner: UNT Libraries Government Documents Department
open access

Design Data for Graphical Construction of Two-Dimensional Sharp-Edge-Throat Supersonic Nozzles

Description: Design data are presented for the graphical construction of two-dimensional sharp-edge-throat supersonic nozzles of minimum length for test-section Mach numbers from 1.20 to 10.00. The method of characteristics used in the design is briefly reviewed.
Date: December 2, 1948
Creator: Shames, Harold & Seashore, Ferris L.
Partner: UNT Libraries Government Documents Department
open access

The Development of Cambered Airfoil Sections Having Favorable Lift Characteristics at Supercritical Mach Numbers

Description: "Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to have lift characteristics at supercritical Mach numbers which are favorable in the sense that the abrupt loss of lift, characteristic of the usual airfoil section at Mach numbers above the critical, is avoided. Aerodynamic characteristics determined, from two-dimensional windtunnel tests at Mach numbers up to approximately 0.9 are presented for each of the derived airfoils. Comparisons are made… more
Date: December 1948
Creator: Graham, Donald J.
Partner: UNT Libraries Government Documents Department
open access

Effect of Compressibility on Normal-Force, Pressure, and Load Characteristics of a Tapered Wing of NACA 66-Series Airfoil Sections With Split Flaps

Description: Note presenting a high-speed wind tunnel investigation of a tapered wing of NACA 66-series airfoil sections equipped with split flaps conducted at Mach numbers up to 0.585 to determine the effects of compressibility on the normal-force, pressure, and load characteristics. Results regarding normal-force characteristics, span-load distribution, pitching-moment characteristics, and flap normal-force and hinge-moment coefficients are provided.
Date: December 1948
Creator: West, F. E., Jr. & Hallissy, J. M., Jr.
Partner: UNT Libraries Government Documents Department
open access

The effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing

Description: "An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing. Longitudinal and lateral stability characteristics were obtained for the model with and without tail surfaces" (p .1).
Date: December 6, 1948
Creator: Spearman, M. Leroy & Becht, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Effect of wing sweep, taper, and thickness ratio on the transonic drag characteristics of wing-body combinations

Description: Report presenting the transonic drag characteristics of a series of wing-body combinations and their component parts using the free-fall method. The configurations examined had wings of various sweeps and thickness ratios mounted on identical bodies of fineness ratio 12.
Date: December 31, 1948
Creator: Thompson, Jim Rogers & Mathews, Charles W.
Partner: UNT Libraries Government Documents Department
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Effects of antispin fillets and dorsal fins on the spin and recovery characteristics of airplanes as determined from free-spinning-tunnel tests

Description: Report presenting the effects of antispin fillets and dorsal fins on the spin and recovery characteristics of airplanes as determined from an analysis of the results of spinning investigations of a large number of models tested in the 15-foot by 20-foot free-spinning tunnels. When antispin fillets were installed on an airplane, the fuselage area below the fillets became more effective in damping the spinning rotation. Results regarding the wake line, shielding of the fillets by the fuselage, an… more
Date: December 1948
Creator: Gale, Lawrence J. & Jones, Ira P., Jr.
Partner: UNT Libraries Government Documents Department
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The effects of variations in Reynolds number between 3.0 x 10 to the power 6 and 25.0 x 10 to the power 6 upon the aerodynamic characteristics of a number of NACA 6-series airfoil sections

Description: The results of an investigation to determine the two-dimensional lift and drag characteristics of nine NACA 6-series airfoil sections at three different Reynolds numbers and a comparison with a different report. The airfoils selected represent sections with variations in thickness, thickness form, and camber.
Date: December 1948
Creator: Loftin, Laurence K., Jr. & Bursnall, William J.
Partner: UNT Libraries Government Documents Department
open access

The flexible rectangular wing in roll at supersonic flight speeds

Description: From Summary: "The problem of the loss in rolling effectiveness at supersonic flight speeds is considered for the case of the rectangular wing. Equations are obtained from which can be calculated either the loss in rate of roll due to flexibility or the torsional stiffness required to maintain a given rate of roll, for two assumed variations of the spanwise distribution of torsional stiffness. A computation form and figures are provided so that calculations can be made without reference to the … more
Date: December 1948
Creator: Tucker, Warren A. & Nelson, Robert L.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of a Combined Geared Unbalancing-Tab and Servotab Control System as Used With an All-Movable Horizontal Tail

Description: Note presenting results of a flight investigation of a Curtiss XP-42 airplane equipped with an all-movable horizontal tail with a control system incorporating a combination of geared unbalancing tabs and servotabs. In order to increase the stick forces for rapid deflections without affecting the forces in gradual maneuvers, the servotab linkage was modified by incorporating a viscous damper in one of the links. An investigation of the arrangement showed that the control characteristics were gen… more
Date: December 1948
Creator: Mungall, Robert G.
Partner: UNT Libraries Government Documents Department
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