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  • Life and Medical Sciences  (6,657)
  • Chemical Engineering  (3,542)
  • AERODYNAMICS  (2,967)
  • STRUCTURAL MECHANICS  (1,910)
  • 1985-1989  (14,711)
  • 1930-1934  (365)
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  • 1
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    Fatigue behavior of 5Ni-Cr-Mo-V steel weldments containing fabrication discontinuities (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The applicability of linear elastic fracture mechanics to characterize the fatigue behavior of high-strength steel weldments containing lack-of-penetration (LOP) and slag/lack-of-fusion (S/LOF) discontinuities is explored. Full penetration, double-V butt welds with reinforcements removed were tested under zero-to-tension axial loading. Various filler metals and welding techniques were used. Both sound welds and welds containing discontinuities were cycled to failure. Where possible, cycles to crack initiation were estimated by strain gage measurements. The fracture mechanics approach was successful in correlating the fatigue lifetimes of specimens containing single LOP discontinuities of varying size. However, the fatigue behavior of specimens containing multiple S/LOF discontinuities proved to be much more complex and difficult to analyze.
    Keywords: STRUCTURAL MECHANICS
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    NASA TECHNICAL REPORTS
  • 2
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    Application of a semianalytical technique for sensitivity analysis of unsteady aerodynamic computations (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: A semianalytical approach is developed for the sensitivity analysis of linear unsteady aerodynamic loads. The semianalytical approach is easier to implement than the analytical approach. It is also computationally less expensive than the finite difference approach when used with panel methods which require a large number of panels. The semianalytical approach is applied to an isolated airfoil in a two-dimensional flow and rotating propfan blades in three-dimensional flow. Sensitivity coefficients with respect to nonshape-dependent variables are shown for some cases.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-2377 , Structures, Structural Dynamics and Materials Conference; Apr 18, 1988 - Apr 20, 1988; Williamsburg, VA; United States
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  • 3
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    Some numerical calculations by using linear classical sonic theories approached from sub- or supersonic speeds (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The unsteady aerodynamics of a two-dimensional wing at sonic speed are studied by using so-called classical sonic theories (linear), approached from supersonic flow (M=1+0) or subsonic flow (M=1-0). In the former approach, the exact expressions of lift and lift distribution are obtained in terms of Fresnel integrals, while in the latter approach an integral equation must be solved, the kernel function of which is obtained from the subsonic Possio's equation and has a root singularity. The discrete analysis is adopted on the basis of the semicircle method (SCM) and the weighting function for subsonic-flow-Gauss-quadrature, as well as modified characteristics obtained from both approaches agree quite well with each other. The results obtained by the present computations are compared with those of DLM-C (subsonic 2D code) developed by ANDO et al, and are found to give a reasonable outer boundary for subsonic unsteady aerodynamics.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20112 , NAS 1.77:20112
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  • 4
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    Postbuckling behavior of fiber reinforced plates and curved panels (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Results obtained on the postbuckling behavior of plates and curved panels using the NOLIN computer program are reported. As an example, the postbuckling behavior of a flexible, isotropic and quadrangular plate is solved and the results are found to be accurate and relibale in comparison with those in the literature. The fatigue-deformation behavior of a rectangular CKL plate is measured, and the results are compared with those from NOLIN and other computer programs. A slightly curved panel with optimized layering is studied.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TT-20094 , NAS 1.77:20094
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  • 5
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    The Aerodynamic Optimization of Wings at Subsonic Speeds and the Influence of Wingtip Design (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Some of the objectives of modern aircraft development are related to the achievement of reduced fuel consumption and aircraft noise. This investigation is mainly concerned with the aerodynamic aspects of aircraft development, i.e., reduction of induced drag. New studies of wing design, and in particular wing tips, are considered. Induced drag is important since, in cruising flight, it accounts for approximately one-third of the entire drag for the aircraft, and one-half while climbing. A survey is presented for the wing geometries and wing tip designs studied, and theoretical investigations of different planar wings with systematically varied wing tip forms are conducted. Attention is also paid to a theoretical study of some planar and nonplanar wings and their comparison with experimental data.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88534 , NAS 1.15:88534
    Format: application/pdf
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  • 6
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    Design of Software for Design of Finite Element for Structural Analysis (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The concepts of software engineering which allow a user of the finite element method to describe a model, to collect and to check the model data in a data base as well as to form the matrices required for a finite element calculation are examined. Next the components of the model description are conceived including the mesh tree, the topology, the configuration, the kinematic boundary conditions, the data for each element, and the loads. The possibilities for description and review of the data are considered. The concept of the segments for the modularization of the programs follows the components of the model description. The significance of the mesh tree as a globular guiding structure will be understood in view of the principle of the unity of the model, the mesh tree, and the data base. The user-friendly aspects of the software system will be summarized: the principle of language communication, the data generators, error processing, and data security.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-88528 , NAS 1.15:88528
    Format: application/pdf
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  • 7
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    Aeronautical engineering: A continuing bibliography with indexes (supplement 225) (1988)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This bibliography lists 429 reports, articles, and other documents introduced into the NASA scientific and technical information system in March, 1988.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(225) , NAS 1.21:7037(225)
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  • 8
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    Finite element calculations for aerodynamic coefficients of a 3-dimensional body in subsonic flow using Green's function method (1988)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An accurate method for evaluating the derivatives along circular paths on the surface is proposed. Calculations are made on various practical configurations such as wing-body combinations, tandem wings, wings with dihedral angles at sideslip, ground effects, interference between a sphere and wind tunnel, etc. Comparisons with experiment show good agreement.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20208 , NAS 1.77:20208
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  • 9
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    Calculation of non-stationary aerodynamic forces in the near sonic range (1988)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The development of a mathematical method for calculating nonstationary supersonic flow in the near-sonic range is described. A perturbation formula is derived based on the exact stationary values; it is applicable to the equation for potential. The problem can thus be divided into stationary and nonstationary fields. The pressure distribution in an oscillating profile is determined, based on hyperbolic differential equations. It is shown that there are important corollaries concerning the application of linear theory. With suitable extrapolations, linear theory can be used up to about Mach 0.8. Linear theory is not applicable, however, when determining the moment coefficients; for this case, a special technique is described.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20310 , NAS 1.77:20310
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  • 10
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    Aeronautical engineering: A continuing bibliography with indexes (supplement 219) (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This bibliography lists 586 reports, articles, and other documents introduced into the NASA scientific and technical information system in October, 1987.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(219) , NAS 1.21:7037(219)
    Format: application/pdf
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