WorldCat Identities

Langley Aeronautical Laboratory

Overview
Works: 1,354 works in 1,722 publications in 1 language and 2,909 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
The results of some theoretical and experimental studies of the vibrations of aircraft wing structures are summarized and discussed. Assessment is made of the importance of various effects not usually included in the elementary theories of bending and torsion of box beams, such as transverse shear flexibility, shear lag, restraint of warping, longitudinal (rotary) inertia, and cross-sectional deformability. The substitute stringer method of incorporating the effects of shear lag into the analysis of box-beam vibration is outlined. Natural frequencies obtained experimentally from resonance tests of box-beam specimens are presented and compared with the results of theoretical calculations, and it is shown that good agreement, particularly for the higher modes, requires the inclusion of secondary effects in the analysis. Two recently developed methods of analysis of low-aspect-ratio wings are described. Frequencies and modes calculated by these two methods are compared with those obtained experimentally for a large-scale builtup delta-wing specimen. (Author)
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
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 6 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
Effect of normal pressure on the critical shear stress of curved sheet by Norman Rafel ( Book )
5 editions published between 1942 and 1945 in English and held by 6 WorldCat member libraries worldwide
Results are presented of tests of two specimens tested to study the effect of normal pressure on the critical compressive stress for thin curved sheets. These specimens are designated by their respective rib spacings of 10 inches and 30 inches. The relationship between compressive stress and normal pressure at which buckles disappeared is independent of whether the buckles were made to disappear by increase of normal pressure or decrease of compressive stress
Comparison of yaw characteristics of a single-engine airplane model with single-rotating and dual-rotating propellers by R. H Neely ( Book )
3 editions published in 1944 in English and held by 6 WorldCat member libraries worldwide
Tests were made n the NACA 29-foot pressure tunnel to determine the yaw characteristics of a 0.32-scale model of a single-engine, fighter-type airplane with six-blade single-rotating and dual-rotating propellers. The propellers used in the investigation were of the same solidity and plan form. Force and moment characteristics of the model, with the exception of the rolling-moment characteristics, are presented for several model and power conditions. Curves are given that show estimated rudder-control characteristics of the design airplane in steady sideslips
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 6 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
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
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 6 WorldCat member libraries worldwide
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
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
An application of statistical data in the development of gust-load criterions by Reginald B Bland ( Book )
1 edition published in 1947 in English and held by 5 WorldCat member libraries worldwide
In conjunction with assumptions concerning the proportion of time spent at various speeds, statistical gust data were used to determine gust load factors that could be exceeded a given number of times during the operational life of an airplane. The results indicated that present gust load factors might be considerably lowered in certain cases with a consequent decrease in structural weight. Modification of the present criterion, however, must await the accumulation of data not presently available
Flight investigation at high mach numbers of several methods of measuring static pressure on an airplane wing by John A Zalovcik ( Book )
3 editions published in 1944 in English and held by 5 WorldCat member libraries worldwide
Summary: A flight investigation was made to compare static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The measurements were made on the upper surface of the wing of the P-47D airplane over a range of flight conditions in which local Mach numbers from 0.34 to 1.41 were obtained at the measurement stations. For some of the tests, a total-pressure tube was mounted on the wing surface to determine its characteristics in supersonic flow. The results indicated that static-pressure measurements obtained with suitably designed and installed flush orifices, static-pressure tubes, and static-pressure belt will be in reasonable agreement for both subsonic and supersonic flow. The pressures in supersonic flow measured by the total-pressure tube mounted on the wing surface were found to be in close agreement with values predicted by theory
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
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
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
Numerical evaluation of the epsilon-integral occurring in the Theodorsen arbitrary airfoil potential theory by Irven Naiman ( Book )
3 editions published in 1944 in English and held by 5 WorldCat member libraries worldwide
Summary: A more precise method of evaluating the [epsilon]-integral occurring in the arbitrary airfoil theory of Theodorsen (NACA Reps. nos. 411 and 452) is developed by retaining higher order terms in the Taylor expansion and by use of Simpson's rule. Formulas are given for routing calculation of the [epsilon]-integral and for the necessary computational coefficients. The computational coefficients are tabulated for a 40-point division of the range of integration from 0 to 2[pi]. With no increase in computational work the systematic error in the numerical value of [epsilon] is reduced from the order of 1 percent to approximately 0.1 percent
Summary of airfoil data by Ira H Abbott ( Book )
2 editions published in 1945 in English and held by 5 WorldCat member libraries worldwide
The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Available data on high-lift devices are presented. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed. The data indicate that the effects of surface condition on the lift and drag characteristics are at least as large as the effects of the airfoil shape and must be considered in airfoil selection and the prediction of wing characteristics. Airfoils permitting extensive laminar flow, such as the NACA 6-series airfoils, have much lower drag coefficients at high speed and cruising lift coefficients than earlier types-of airfoils if, and only if, the wing surfaces are sufficiently smooth and fair. The NACA 6-series airfoils also have favorable critical-speed characteristics and do not appear to present unusual problems associated with the application of high-lift and lateral-control devices. Much of the data given in the NACA Advance Confidential Report entitled "Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Number and Low Turbulence," by Eastman N. Jacobs, Ira R. Abbott, and Milton Davidson, March 1942 has been corrected and included in the present paper, which supersedes the previously published paper
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
Effects of yaw and pitch motion on model attitude measurements by Ping Tcheng ( Book )
2 editions published in 1995 in English and held by 5 WorldCat member libraries worldwide
 
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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
United States National Advisory Committee for Aeronautics Langley Memorial Aeronautical Laboratory
Languages
English (57)