United States National Advisory Committee for Aeronautics
Overview
Works:  10,563 works in 12,720 publications in 1 language and 60,055 library holdings 

Genres:  Bibliography History Abstracts Periodicals Mathematical formulae 
Roles:  Other, Editor 
Classifications:  TL521.3, 629.1 
Publication Timeline
.
Most widely held works about
United States
 Expanding the envelope : flight research at NACA and NASA by Michael H Gorn( )
 Breaking the chains of gravity : the story of spaceflight before NASA by Amy Shira Teitel( Book )
 Orders of magnitude : a history of the NACA and NASA, 19151990 by Roger E Bilstein( Book )
 The highspeed frontier : case histories of four NACA programs, 19201950 by John Vernon Becker( Book )
 Testing aircraft, exploring space : an illustrated history of NACA and NASA by Roger E Bilstein( Book )
 Model research : the National Advisory Committee for Aeronautics, 19151958 by Alex Roland( Book )
 NASA's first A : aeronautics from 1958 to 2008 by Robert G Ferguson( )
 Model research : volumes 1 & 2 by Alex Roland( Book )
 NASA Technical Reports Server : NTRS by United States( )
 Emblems of exploration : logos of the NACA and NASA by Joseph R Chambers( )
 The first century of flight : NACA/NASA contributions to aeronautics( Visual )
 NACA : National Advisory Committee for Aeronautics( )
 Orders of magnitude : a history of NACA and NASA, 19151976 by Frank Walter Anderson( Book )
 Annual report of the National Advisory Committee for Aeronautics by United States( )
 Frontiers of flight, the story of NACA research by George W Gray( Book )
 Index of NACA technical publications by United States( )
 The National Advisory Committee for Aeronautics : an annotated bibliography by Alice R Buchalter( )
 Aeronautics in NACA and NASA( Book )
 Aeronautics and astronautics : an American chronology of science and technology in the exploration of space, 19151960 by United States( )
 19171992, 75 years NACA NASA Langley Research Center( Book )
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Most widely held works by
United States
Orders of magnitude : a history of NACA and NASA, 19151980 by
Frank Walter Anderson(
Book
)
2 editions published in 1981 in English and held by 294 WorldCat member libraries worldwide
2 editions published in 1981 in English and held by 294 WorldCat member libraries worldwide
Handbook of structural stability by
George Gerard(
)
4 editions published between 1957 and 1995 in English and held by 217 WorldCat member libraries worldwide
The cases which exhibit a marked disagreement between linear theory and test data include those of curved plates and cylinders under axial compression, cylinders under bending, and spherical plates under external pressure. These cases have been analyzed by a unified semiempirical approach for both the elastic and inelastic ranges which is satisfactory for analysis and design purposes
4 editions published between 1957 and 1995 in English and held by 217 WorldCat member libraries worldwide
The cases which exhibit a marked disagreement between linear theory and test data include those of curved plates and cylinders under axial compression, cylinders under bending, and spherical plates under external pressure. These cases have been analyzed by a unified semiempirical approach for both the elastic and inelastic ranges which is satisfactory for analysis and design purposes
Technical memorandum by
United States(
)
in English and Undetermined and held by 151 WorldCat member libraries worldwide
Chiefly translations from foreign aeronautical journals
in English and Undetermined and held by 151 WorldCat member libraries worldwide
Chiefly translations from foreign aeronautical journals
Stresses around rectangular cutouts in skinstringer panels under axial loads  2 by
Paul Kuhn(
)
4 editions published in 1943 in English and held by 127 WorldCat member libraries worldwide
Cutouts in wings or fuselages produce stress concentrations that present a serious problem to the stress analyst. As a partial solution of the general problem, this paper presents formulas for calculating the stress distribution around rectangular cutouts in axially loaded panels. The formulas are derived by means of the substitutestringer method of shearlag analysis
4 editions published in 1943 in English and held by 127 WorldCat member libraries worldwide
Cutouts in wings or fuselages produce stress concentrations that present a serious problem to the stress analyst. As a partial solution of the general problem, this paper presents formulas for calculating the stress distribution around rectangular cutouts in axially loaded panels. The formulas are derived by means of the substitutestringer method of shearlag analysis
Critical combinations of longitudinal and transverse direct stress for an infinitely long flat plate with edges elastically
restrained against rotation by
S. B Batdorf(
)
4 editions published in 1946 in English and held by 126 WorldCat member libraries worldwide
A theoretical Investigation was made of the buckling of an infinitely long flat plate with edges elastically restrained against rotation under combinations of longitudinal are presented that give the critical combinations of stress for several different degrees of elastic edge restraints Including simple support and complete fixity. It was found that an appreciable fraction of the critical longitudinal stress may be applied to the plate without any reduction in the transverse compressive stress required for buckling
4 editions published in 1946 in English and held by 126 WorldCat member libraries worldwide
A theoretical Investigation was made of the buckling of an infinitely long flat plate with edges elastically restrained against rotation under combinations of longitudinal are presented that give the critical combinations of stress for several different degrees of elastic edge restraints Including simple support and complete fixity. It was found that an appreciable fraction of the critical longitudinal stress may be applied to the plate without any reduction in the transverse compressive stress required for buckling
Description of stressstrain curves by three parameters by
Walter Ramberg(
)
3 editions published between 1943 and 1947 in English and held by 121 WorldCat member libraries worldwide
A simple formula is suggested for describing the stressstrain curve in terms of three parameters: namely, Young's modulus and two secant yield strengths. Dimensionless charts are derived from this formula for determining the stressstrain curve, the tangent modulus, and the reduced modulus of a material for which these three parameters are given. Comparison with the tensile and compressive data on aluminum alloy, stainlesssteel, and carbonsteel sheet in NACA Technical Note No. 840 indicates that the formula is adequate for most of these materials. The formula does not describe the behavior of alclade sheet, which shows a marked change in slope at low stress. It seems probable that more than three parameters will be necessary to represent such stressstrain curves adequately
3 editions published between 1943 and 1947 in English and held by 121 WorldCat member libraries worldwide
A simple formula is suggested for describing the stressstrain curve in terms of three parameters: namely, Young's modulus and two secant yield strengths. Dimensionless charts are derived from this formula for determining the stressstrain curve, the tangent modulus, and the reduced modulus of a material for which these three parameters are given. Comparison with the tensile and compressive data on aluminum alloy, stainlesssteel, and carbonsteel sheet in NACA Technical Note No. 840 indicates that the formula is adequate for most of these materials. The formula does not describe the behavior of alclade sheet, which shows a marked change in slope at low stress. It seems probable that more than three parameters will be necessary to represent such stressstrain curves adequately
Buckling of thinwalled cylinder under axial compression and internal pressure by Hsu Lo(
)
2 editions published in 1950 in English and held by 119 WorldCat member libraries worldwide
An investigation was made of a thinwalled cylinder under axial compression and various internal pressures to study the effect of the internal pressure on the compressive buckling stress of the cylinder. A theoretical analysis based on a largedeflection theory was also made. The theoretically predicted increase of compressive buckling stress due to internal pressure agrees fairly well with the experimental results
2 editions published in 1950 in English and held by 119 WorldCat member libraries worldwide
An investigation was made of a thinwalled cylinder under axial compression and various internal pressures to study the effect of the internal pressure on the compressive buckling stress of the cylinder. A theoretical analysis based on a largedeflection theory was also made. The theoretically predicted increase of compressive buckling stress due to internal pressure agrees fairly well with the experimental results
Shear lag in box beams methods of analysis and experimental investigations by
Paul Kuhn(
)
4 editions published between 1941 and 1942 in English and held by 118 WorldCat member libraries worldwide
The bending stresses in the covers of box beams or wideflange beams differ appreciably from the stresses predicted by the ordinary bending theory on account of shear deformation of the flanges. The problem of predicting these differences has become known as the shearlag problem. The first part of this paper deals with methods of shearlag analysis suitable for practical use. The second part of the paper describes straingage tests made by the NACA to verify the theory. Three tests published by other investigators are also analyzed by the proposed method. The third part of the paper gives numerical examples illustrating the methods of analysis. 
4 editions published between 1941 and 1942 in English and held by 118 WorldCat member libraries worldwide
The bending stresses in the covers of box beams or wideflange beams differ appreciably from the stresses predicted by the ordinary bending theory on account of shear deformation of the flanges. The problem of predicting these differences has become known as the shearlag problem. The first part of this paper deals with methods of shearlag analysis suitable for practical use. The second part of the paper describes straingage tests made by the NACA to verify the theory. Three tests published by other investigators are also analyzed by the proposed method. The third part of the paper gives numerical examples illustrating the methods of analysis. 
Deformation analysis of wing structures by
Paul Kuhn(
)
2 editions published in 1947 in English and held by 118 WorldCat member libraries worldwide
The elementary theories of bending and torsion often do not describe the stresses in aircraft shell structures with adequate accuracy; more refined stress theories have therefore have developed over a period of years. Theories of this nature are applied to the problem of calculating the deflections, particularly of wings. Bending as well as torsional deflections are discussed for wings without or with cutouts. Whenever convenient, the formulas are given in such a form that they yield corrections to be added to the deflections calculated by means of the elementary theories. Examples show that the deflection corrections usually are quite small; very simple approximation formulas are therefore adequate for design purposes when conventional structures uder a reasonably uniform loading are being considered
2 editions published in 1947 in English and held by 118 WorldCat member libraries worldwide
The elementary theories of bending and torsion often do not describe the stresses in aircraft shell structures with adequate accuracy; more refined stress theories have therefore have developed over a period of years. Theories of this nature are applied to the problem of calculating the deflections, particularly of wings. Bending as well as torsional deflections are discussed for wings without or with cutouts. Whenever convenient, the formulas are given in such a form that they yield corrections to be added to the deflections calculated by means of the elementary theories. Examples show that the deflection corrections usually are quite small; very simple approximation formulas are therefore adequate for design purposes when conventional structures uder a reasonably uniform loading are being considered
Critical stress of thinwalled cylinders in torsion by
S. B Batdorf(
)
3 editions published in 1947 in English and held by 117 WorldCat member libraries worldwide
A theoretical solution is given of the critical stress of thinwalled cylinders loaded in torsion. The results are presented in terms of a few simple formulas and curves which are applicable to a wide range of cylinder dimensions from very short cylinders of large radius to long cylinders of small radius. Theoretical results are found to be in somewhat better agreement with experimental results than previous theoretical work for the same range of cylinder dimensions
3 editions published in 1947 in English and held by 117 WorldCat member libraries worldwide
A theoretical solution is given of the critical stress of thinwalled cylinders loaded in torsion. The results are presented in terms of a few simple formulas and curves which are applicable to a wide range of cylinder dimensions from very short cylinders of large radius to long cylinders of small radius. Theoretical results are found to be in somewhat better agreement with experimental results than previous theoretical work for the same range of cylinder dimensions
The influence of impact velocity on the tensile characteristics of some aircraft metals and alloys by
Donald S Clark(
)
2 editions published in 1942 in English and held by 116 WorldCat member libraries worldwide
This report deals principally with the results of tension tests on sixteen metals and alloys, most of which are employed extensively in aircraft construction. The tension characteristics are discussed for static conditions and rates of deformation up to about 150 feed per second
2 editions published in 1942 in English and held by 116 WorldCat member libraries worldwide
This report deals principally with the results of tension tests on sixteen metals and alloys, most of which are employed extensively in aircraft construction. The tension characteristics are discussed for static conditions and rates of deformation up to about 150 feed per second
Bending of rectangular plates with large deflections by
Qi Wang(
)
2 editions published in 1948 in English and held by 116 WorldCat member libraries worldwide
This document presents the solution of Von Karman equations for thin plates with large deflections for special cases of rectangular plates of 1.5 and 2.0 lengthwidth ratios under uniform normal pressure. The boundary conditions approximate panels with riveted edges under normal pressure greater than that of the surrounding panels. Center deflections (to twice the plate thickness), membrane stresses, and extremefiber bending stresses are given as functions of the pressure. For small deflections, the results are consistent with those given by Timoshenko
2 editions published in 1948 in English and held by 116 WorldCat member libraries worldwide
This document presents the solution of Von Karman equations for thin plates with large deflections for special cases of rectangular plates of 1.5 and 2.0 lengthwidth ratios under uniform normal pressure. The boundary conditions approximate panels with riveted edges under normal pressure greater than that of the surrounding panels. Center deflections (to twice the plate thickness), membrane stresses, and extremefiber bending stresses are given as functions of the pressure. For small deflections, the results are consistent with those given by Timoshenko
Critical combinations of torsion and direct axial stress for thinwalled cylinders by
S. B Batdorf(
)
2 editions published in 1947 in English and held by 116 WorldCat member libraries worldwide
A theoretical solution is presented for the determination of the combinations of direct axial stress and torsion which cause thinwalled cylinders with either simply supported or clamped edges to buckle. This theoretical solution is used in conjunction with available test data to develop empirical curves and formulas for use in design. Comparisons are made with theoretical and empirical solutions obtained in other investigations
2 editions published in 1947 in English and held by 116 WorldCat member libraries worldwide
A theoretical solution is presented for the determination of the combinations of direct axial stress and torsion which cause thinwalled cylinders with either simply supported or clamped edges to buckle. This theoretical solution is used in conjunction with available test data to develop empirical curves and formulas for use in design. Comparisons are made with theoretical and empirical solutions obtained in other investigations
Some investigations of the general instability of stiffened metal cylinders. 8  Stiffened metal cylinders subjected to pure
torsion by
Louis Dunn(
)
4 editions published in 1947 in English and held by 115 WorldCat member libraries worldwide
An experimental investigation of the general instability of reinforced thinwalled metal cylinders was carried out at the California Institute of Technology. The basic parameters involved were the spacing and sectional properties of stiffening elements, the wall thickness, and the diameter of the cylinder. An analysis of the experimental data led to a suitable parameter for estimating the generalinstability stress of reinforced metal cylinders when subjected to pure torsion loading
4 editions published in 1947 in English and held by 115 WorldCat member libraries worldwide
An experimental investigation of the general instability of reinforced thinwalled metal cylinders was carried out at the California Institute of Technology. The basic parameters involved were the spacing and sectional properties of stiffening elements, the wall thickness, and the diameter of the cylinder. An analysis of the experimental data led to a suitable parameter for estimating the generalinstability stress of reinforced metal cylinders when subjected to pure torsion loading
A Method of calculating the compressive strength of Zstiffened panels that develop local instability by George L Gallaher(
)
2 editions published in 1947 in English and held by 115 WorldCat member libraries worldwide
A method, based on the elastic theory for plate buckling and test results for 24ST aluminumalloy Zstiffened panels, is shown for calculating the compressive strength of Zstiffened panels that develop local instability. This method can be used to calculate the critical compressive stress above, as well as within, the elastic range. For stresses above threefourths the compressive yield stress the method can be used for the approximate determination of the average compressive stress at maximum load
2 editions published in 1947 in English and held by 115 WorldCat member libraries worldwide
A method, based on the elastic theory for plate buckling and test results for 24ST aluminumalloy Zstiffened panels, is shown for calculating the compressive strength of Zstiffened panels that develop local instability. This method can be used to calculate the critical compressive stress above, as well as within, the elastic range. For stresses above threefourths the compressive yield stress the method can be used for the approximate determination of the average compressive stress at maximum load
Nonlinear largedeflection boundaryvalue problems of rectangular plates by
Qi Wang(
)
2 editions published in 1948 in English and held by 115 WorldCat member libraries worldwide
Relaxation and successive approximation methods are used to solve Von Karman's equations as applied to initially flat, rectangular plates with large deflections under either normal pressure or combined normal pressure and side thrust, and several specific cases are analyzed. The general method developed may be applied to bending and combined bending and buckling problems with practically any boundary conditions to any required degree of accuracy or applied to solve the membrane theory of the plate which applies when the deflection is very large in comparison with the thickness of the plate
2 editions published in 1948 in English and held by 115 WorldCat member libraries worldwide
Relaxation and successive approximation methods are used to solve Von Karman's equations as applied to initially flat, rectangular plates with large deflections under either normal pressure or combined normal pressure and side thrust, and several specific cases are analyzed. The general method developed may be applied to bending and combined bending and buckling problems with practically any boundary conditions to any required degree of accuracy or applied to solve the membrane theory of the plate which applies when the deflection is very large in comparison with the thickness of the plate
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Related Identities
 Langley Aeronautical Laboratory
 United States National Aeronautics and Space Administration
 Gorn, Michael H. Author
 Ames Research Center
 Aircraft Engine Research Laboratory
 Bilstein, Roger E. Author
 Stein, Manuel Author
 Batdorf, S. B. Author
 United States National Aeronautics and Space Administration Scientific and Technical Information Branch
 Lewis Flight Propulsion Laboratory
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Aerodynamics AerodynamicsResearch Aeronautics Aeronautics, Commercial Aeronautics, Military Aeronautics and state AeronauticsBibliography AeronauticsResearch AirplanesDesign and construction AirplanesFlight testing AirplanesMaterialsTesting AirplanesMotors AirplanesWings Astronautics AstronauticsResearch Axial loads Bending Boundary value problems Buckling (Mechanics) Charts, diagrams, etc Cylinders Elasticity Exploration of outer space Germany Highspeed aeronauticsResearch Holes Insignia Langley Research Center Loads (Mechanics) Mathematical analysis Mathematics Medals Outer space Plates (Engineering) Reinforcing bars Relaxation methods (Mathematics) Rocketry Rockets (Aeronautics) Science Shear (Mechanics) Space flight Space race Space sciencesResearch Sputnik satellites Strains and stresses Thinwalled structures Torsion United States United States.National Advisory Committee for Aeronautics United States.National Aeronautics and Space Administration
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Alternative Names
United States. National Aeronautics and Space Administration
Advisory Committee for Aeronautics
Advisory Committee for Aeronautics United States
Amerika gasshukoku koku shimon iinkai
ÉtatsUnis. Advisory Committee for Aeronautics
Jungtinės Valstijos National Advisory Committee for Aeronautics
N.A.C.A.
NACA
NACA (National Advisory Committee for Aeronautics)
Nacionalni savetodavni komitet za aeronautiku
National advisory committee for aeronautics
National Advisory Committee for Aeronautics agence fédérale américaine, précédant la NASA
National Advisory Committee for Aeronautics (É.U.)
National Advisory Committee for Aeronautics (Estados Unidos)
National Advisory Committee for Aeronautics (Forente stater)
National Advisory Committee for Aeronautics organisatie uit Verenigde Staten van Amerika
National Advisory Committee for Aeronautics (U.S.)
National Advisory Committee for Aeronautics United States
Nationaler Beratungsausschuß für Luftfahrt United States
Pwyllgor Cynghori Cenedlaethol ar Awyrennau
Riiklik Aeronautika Nõuandekomitee
United States Advisory Committee for Aeronautics
United States Aeronautics, National Advisory Committee for
United States. National Advisory Committee for Aeronautics
United States Nationaler Beratungsausschuß für Luftfahrt
Национални саветодавни комитет за аеронаутику
Национальный консультативный комитет по воздухоплаванию
Національний консультативний комітет з повітроплавання
הוועדה הלאומית המייעצת לאווירונאוטיקה
اللجنة الاستشارية الوطنية للملاحة الجوية
کمیته رایزنی ملی هوانوردی آمریکا
தேசிய வானூர்தியியல் ஆலோசனை செயற்குழு
നാഷണൽ അഡ്വൈസറി കമ്മിറ്റി ഫോർ എയറോനോട്ടിക്സ്
미국 국가항공자문위원회
アメリカ ガッシュウコク コウクウ シモン イインカイ
アメリカ航空諮問委員会
全米航空諮問委員会
美國國家航空諮詢委員會
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