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  • Other Sources  (188)
  • AERODYNAMICS  (97)
  • FLUID MECHANICS AND HEAT TRANSFER  (43)
  • STRUCTURAL MECHANICS  (41)
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  • 1975-1979  (188)
  • 1955-1959
  • 1975  (188)
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  • Other Sources  (188)
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  • 1975-1979  (188)
  • 1955-1959
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  • 1
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    Stability analysis of nonlinear autonomous systems - General theory and application to flutter (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The analysis makes use of a singular perturbation method, the multiple time scaling. Concepts of stable and unstable limit cycles are introduced. The solution is obtained in the form of an asymptotic expansion. Numerical results are presented for the nonlinear flutter of panels and airfoils in supersonic flow. The approach used is an extension of a method for analyzing nonlinear panel flutter reported by Morino (1969).
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 75-102 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
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  • 2
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    Aerodynamic drag reduction tests on a full-scale tractor-trailer combination and a representative box-shaped ground vehicle (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: AERODYNAMICS
    Type: SAE PAPER 750703 , West Coast Meeting; Aug 11, 1975 - Aug 14, 1975; Seattle, WA
    Format: text
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  • 3
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    On the calculation of supersonic separating and reattaching flows (1975)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: A method is developed for solving the laminar and turbulent compressible boundary layer equations for separating and reattaching flows. Results of this method are compared with experimental data for two laminar and three turbulent layer, shock wave interactions. Several Navier-Stokes solutions are obtained for each of the laminar boundary layer, shock wave interactions considered. Comparison of these solutions indicates a first order sensitivity in C sub f to the computational mesh selected in both the viscous and inviscid portions of the flow. Comparison of the present boundary layer solutions with the Navier-Stokes solutions and with data for a given Mach number indicates that as long as the separation bubble is small, the boundary layer approximation yields solutions whose accuracy is comparable to the Navier-Stokes solutions.
    Keywords: AERODYNAMICS
    Type: AGARD Flow Separation; 12 p
    Format: text
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  • 4
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    Experimental verification of turbulent skin friction reduction with compliant walls (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Preliminary compliant wall skin friction test results obtained in a low-turbulence pressure tunnel are reported. Compliant surface skins consisted of 0.0025 cm thick mylar, stretched under tension and area-bonded or longitudinally strip-bonded with silicone rubber adhesive to polyurethane foam. Mean velocity and fluctuating survey data were obtained with a single slanted hot wire. Mean velocity profiles for the area-bonded mylar surface skins indicated up to a 20% reduction in boundary-layer thickness (and lower momentum thickness) over rigid surfaces. This reduction in boundary-layer thickness indicates that a drag reduction occurred. In addition, a 16% reduction in wall shear was evident for the mylar/compressor foam compliant surface.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; July 197
    Format: text
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  • 5
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    The automated multi-stage substructuring system for NASTRAN (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The substructuring capability developed for eventual installation in Level 16 is now operational in a test version of NASTRAN. Its features are summarized. These include the user-oriented, Case Control type control language, the automated multi-stage matrix processing, the independent direct access data storage facilities, and the static and normal modes solution capabilities. A complete problem analysis sequence is presented with card-by-card description of the user input.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 571-591
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  • 6
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    Simulation of turbulent transonic separated flow over an airfoil (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A code developed for simulating high Reynolds number transonic flow fields of arbitrary configuration is described. This code, in conjunction with laboratory experiments, is used to devise and test turbulence transport models which may be suitable in the prediction of such flow fields, with particular emphasis on regions of flow separation. The solutions describe the flow field, including both the shock-induced and trailing-edge separation regions, in sufficient detail to provide the profile and friction drag.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 419-436
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  • 7
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    On the calculation of supersonic, separating, and reattaching flows (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A method is developed for solving the laminar and turbulent compressible boundary-layer equations for separating and reattaching flows. Results of this method are compared with experimental data for two laminar and three turbulent boundary-layer, shock-wave interactions. Several Navier-Stokes solutions were obtained for each of the laminar boundary-layer, shock-wave interactions considered. Comparison of these solutions indicates a first-order sensitivity in C sub f to the computational mesh selected in both the viscous and inviscid portions of the flow.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 151-175
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  • 8
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    Long fluid filled bags suspended by line forces (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A previous analysis of fluid filled storage bags is extended to the case of a long fluid filled cylindrical membrane supported by uniform line loads. Cross-sectional shape, stiffness of the support system and stress resultants in the membrane are determined. The application of the numerical results to problems arising in the design of nonrigid airships is discussed.
    Keywords: AERODYNAMICS
    Type: MIT Proc. of the Interagency Workshop on Lighter than Air Vehicles; p 199-208
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  • 9
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    A comparison of a shock-capturing technique with experimental data for three-dimensional internal flows (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Shock-capturing solutions for an axisymmetric supersonic inlet at small angles of attack are obtained. Good overall agreement between the shock-capturing solutions and experimental data is shown except in regions of strong viscous effects or boundary-layer removal. Although the results indicate a strong potential for the use of shock-capturing or finite-difference solutions for internal flows, improvement in the ability to handle the reflection of strong shockwaves having downstream Mach numbers near 1 is needed.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 623-642
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  • 10
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    NASTRAN applications to aircraft propulsion systems (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of NASTRAN in propulsion system structural integration analysis is described. Computer support programs for modeling, substructuring, and plotting analysis results are discussed. Requirements on interface information and data exchange by participants in a NASTRAN substructure analysis are given. Static and normal modes vibration analysis results are given with comparison to test and other analytical results.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 91-104
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