WorldCat Identities

Langley Aeronautical Laboratory

Overview
Works: 1,440 works in 1,980 publications in 1 language and 2,999 library holdings
Genres: History 
Classifications: TL672, 629.1
Publication Timeline
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Publications about Langley Aeronautical Laboratory Publications about Langley Aeronautical Laboratory
Publications by Langley Aeronautical Laboratory Publications by Langley Aeronautical Laboratory
Most widely held works by Langley Aeronautical Laboratory
Recent research on the determination of natural modes and frequencies of aircraft wing structures by Langley Aeronautical Laboratory ( Book )
2 editions published in 1956 in English and held by 31 WorldCat member libraries worldwide
Aerodynamic theory and its application to flutter by Langley Aeronautical Laboratory ( Book )
1 edition published in 1956 in English and held by 29 WorldCat member libraries worldwide
Performance of a high-speed compression-ignition engine using multiple orifice fuel injection nozzles by J. A Spanogle ( Book )
1 edition published in 1930 in English and held by 7 WorldCat member libraries worldwide
This report presents the test results during an investigation to determine the relative performance of a single-cylinder, high-speed, compression-ignition engine when using fuel injection valve nozzles with different numbers, sizes, and directions of round orifices. A spring-loaded, automatic injection value was used, centrally located at the top of a vertical disk-type combustion chamber formed between horizontally opposed inlet and exhaust valves of a 5-inch by 7-inch engine
Tests of related forward-camber airfoils in the variable-density wind tunnel by Eastman N Jacobs ( Book )
3 editions published between 1937 and 1938 in English and held by 6 WorldCat member libraries worldwide
A preliminary investigation of aerodynamic characteristics of small inclined air outlets at transonic Mach numbers by Paul E Dewey ( Book )
2 editions published between 1953 and 1955 in English and held by 5 WorldCat member libraries worldwide
The aerodynamic characteristics of several outlets with inclined or curved axes discharging air into a transonic stream have been investigated. The data presented herein show the discharge coefficient of such outlets and the static-pressure distribution in the vicinity of the outlets for several values of stream Mach number and discharge flow parameter. Tuft observations, showing the vortex formations caused by the outlet discharge from a perpendicular and an inclinded outlet, are also presented
Supersonic wave interference affecting stability by Eugene S Love ( Book )
1 edition published in 1958 in English and held by 5 WorldCat member libraries worldwide
Some of the significant interference fields that may affect stability of aircraft at supersonic speeds are briefly summarized. Illustrations and calculations are presented to indicate the importance of interference fields created by wings, bodies, wing-body combinations, jets, and nacelles
Summary of recent theoretical and experimental work on box-beam vibrations by John M Hedgepeth ( Book )
2 editions published in 1955 in English and held by 5 WorldCat member libraries worldwide
A discussion of various secondary effects which have an important influence on the vibration characteristics of box beams is presented. Means of incorporating these effects in vibration analyses of actual built-up box beams are discussed. Comparisons with experiment are given; good agreement between theory and experiment is obtained when the secondary effects are included
Method for calculating wing characteristics by lifting-line theory using nonlinear section life data by James C Sivells ( Book )
1 edition published in 1947 in English and held by 5 WorldCat member libraries worldwide
The wing characteristics calculated from general nonlinear section lift data have been found to agree much closer with experimental data in the region of maximum lfit coefficient than those calculated on the assumption of linear section lift curves. The calculations are subject to the limitations of lifting-line theory and should not be expected to give accurate results for wings of low aspect ratio and large amounts of sweep
Flight tests of a helicopter in autorotation, including a comparison with theory by Alfred Gessow ( Book )
1 edition published in 1947 in English and held by 5 WorldCat member libraries worldwide
The results of glide performance tests conducted on a test helicopter with its original production blades in the autorotation condition are presented. The data were reduced to coefficient form, and performance at standard sea-level conditions was calculated. The experimentally determined rotor drag-lift ratios were compared with theoretical calculations, and a similar comparison was made for previously obtained power-on flight data. In addition, the improvement in power-off (autorotation) performance that results from operating with aerodynamically cleaner blades was investigated
Axial-flow fan and compressor blade design data at 52.5 ╠Őstagger and further verification of cascade data by rotor tests by Seymour M Bogdonoff ( Book )
1 edition published in 1947 in English and held by 5 WorldCat member libraries worldwide
Previous tests of blower-blade sections have been extended by a series of tests at 52.5 degrees stagger. The results of these tests have been combined with the earlier test results and are presented in new blade design charts which supersede those previously presented. An investigation in a test blower over a range of stagger from 44 degrees to 65 degrees has shown that for blades at a solidity of 1.0, the two-dimensional cascade data predict the turning angle to within 1/2 degree
Interference of wing and fuselage from tests of 30 combinations with triangular and elliptical fuselages in the NACA variable-density tunnel by Albert Sherman ( Book )
1 edition published in 1947 in English and held by 5 WorldCat member libraries worldwide
Tests of 12 wing-fuselage combinations employing triangluar and 18 employing elliptical fuselages were made in the NACA variable-density tunnel as a part of a program to investigate at large values of Reynolds number the aerodynamic effects of wing-fuselage interference. This program is outined in NACA Report no. 540, which contains the test results for 209 combinations, 202 with round and 7 with rectangular fuselages, comprising the basic part of the wing-fuselage interference investigation
Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes by Marvin Pitkin ( Book )
in English and held by 5 WorldCat member libraries worldwide
An analysis has been made of factors affecting the net lift increment attainable with trailing-edge split flaps on tailless airplanes. The flaps investigated in the analysis were designed to contribute zero pitching moments about the wing aerodynamic center when deflected. Calculations were made of the lift and pitching-moment characteristics of flaps of this type over a range of design conditions in which sweepback angle, aspect ratio, taper ratio, flap chord, and flap deflection were widely varied. In addition, calculations were made to determine the effect of the various parameters upon the loss in lift incurred in trimming the stability moments of a tailless airplane. A method is given for roughly estimating the maximum lift coefficient of tailless airplanes
Jet aircraft engine emissions database development 1992 military, charter, and nonscheduled traffic by Munir Metwally ( Book )
1 edition published in 1995 in English and held by 5 WorldCat member libraries worldwide
An electromagnetic-analogy method of solving lifting-surface-theory problems by Robert S Swanson ( Book )
3 editions published in 1945 in English and held by 5 WorldCat member libraries worldwide
A method is suggested for making lifting-surface calculations by means of magnetic measurements of an electromagnetic-analogy model. The method is based on the perfect analogy between the strength of the magnetic field around a conductor and the strength of the induced-velocity field around a vortex. Electric conductors are arranged to represent the vortex sheet. The magnetic-field strength is determined by measuring, with an electronic voltmeter, the voltage induced in a small search coil by the alternating current in the wires representing the vortex sheet. Solutions of nonlinear lifting-surface problems may be obtained by placing the conductors representing the trailing vortices along the fluid lines (Helmholtz condition). A potential-flow solution for the distortion and rolling up of the trailing-vortex sheet may be obtained. By use of the Prandtl-Glauert rule, the lifting-surface theory may be adapted to include first-order compressibility effects
Investigation at supersonic speeds of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag of seven boattail bodies of revolution designed for minimum wave drag by August F Bromm ( Book )
2 editions published between 1953 and 1956 in English and held by 5 WorldCat member libraries worldwide
An investigation has been conducted in the Langley 9-inch supersonic tunnel to determine the effect of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag at zero lift of seven boattail bodies of revolution designed for minimum wave drag according to NACA Technical Note 2550. The investigation covered a Reynolds number range from approximately 1,000,000 to 10,000,000 at Mach numbers of 1.62, 1.93, and 2.41, respectively. The results show that base drag and, in general, the total drag increase with increasing values of the ratio of base area to maximum area B/S(max), although the results reported in NACA Technical Note 3054 showed that the wave drag decreased with ticreasing values of B/S(max). The laminar skin-friction drag is in agreement with the theoretical predictions used, and, within the Mach number range of these tests, the simple Blasius incompressible theory gives a satisfactory prediction. Except for values of B/S(max) near 1, the Reynolds number of transition increases with increasing Mach number and, as this ratio approaches 1, this variation is seen to reverse. These variations in Reynolds number of transition with Mach number appear to be associated with the changes in pressure gradient over the rear of the bodies
Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957 by Martin R Copp ( Book )
2 editions published in 1958 in English and held by 5 WorldCat member libraries worldwide
A summary of the locations, extents, and intensities of turbulent areas encountered during a flight investigation of the jet stream is presented. The data were obtained from NACA VGH time-history records
Experimental and theoretical determination of thermal stresses in a flat plate by Richard R Heldenfels ( Book )
2 editions published in 1952 in English and held by 5 WorldCat member libraries worldwide
Thermal stresses induced in a flat, rectangular, 75S-T6 aluminum-alloy plate by nonuniform heating are determined both experimentally and theoretically. The characteristics of commercially available bonded resistance wire strain gages are first investigated to determine their suitability for measuring stresses under simple conditions of stress and temperature. The gages are then used to measure thermal stresses in the flat plate in order to study their suitability under more complicated conditions. The experimental results are found to be in satisfactory agreement (within plus or minus 5 percent of maximum calculated stress) with an approximate theoretical solution of the problem
Surface heat-transfer coefficients of finned cylinders by Herman H Ellerbrock ( )
2 editions published between 1939 and 1940 in English and held by 5 WorldCat member libraries worldwide
A brief history of aeronautics, as pictured on the murals in the rotunda of the Administration Building, Langley Memorial Aeronautical Laboratory by Julius J Lankes ( Book )
1 edition published in 1946 in English and held by 5 WorldCat member libraries worldwide
The use of large valve overlap in scavenging a supercharged spark-ignition engine using fuel injection by Oscar W Schey ( Book )
1 edition published in 1932 in English and held by 5 WorldCat member libraries worldwide
This investigation was conducted to determie the effect of more complete scavenging on the full throttle power and the fuel consumption of a four-stroke-cycle engine. The test engine was scavenged by using a large valve overlap and maintaining a pressure in the inlet manifold of 2 inches of mercury above the atmospheric. The maximum valve overlap used was 112 degrees. The results of the tests showe that the clearance volume of an engine can be scavenged by using a large valve overlap and about 2 to 5 inches of mercury pressure difference between the inlet and exhaust valve. With a fuel-injection system when the clearance volume was scavenged, a b.m.e.p. of over 185 pounds per square inch and fuel consumption of 0.45 pound per brake horsepower per hour were obtained with a 6.5 compression ratio. An increase of approximately 10 pounds per square inch b.m.e.p. was obtained with a fuel-injection system over that with a carburetor
 
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Alternative Names

controlled identity Langley Research Center

Hampton (Va.). Langley Aeronautical Laboratory
Langley Air Force Base (Va.). Langley Aeronautical Laboratory
Langley Memorial Aeronautical Laboratory
United States. Langley Aeronautical Laboratory
United States. Langley Aeronautical Laboratory, Hampton, Va.
United States. Langley Memorial Aeronautical Laboratory
United States. National Advisory Committee for Aeronautics. Langley Aeronautical Laboratory
USA National Advisory Committee for Aeronautics Langley Memorial Aeronautical Laboratory
Languages
English (51)