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  • Aerodynamics  (4)
  • FLUID MECHANICS AND HEAT TRANSFER  (1)
  • Theoretical Mathematics; Statistics and Probability; Aerodynamics  (1)
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  • 1
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    Simultaneous Aerodynamic Analysis and Design Optimization (SAADO) for a 3-D Flexible Wing (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The formulation and implementation of an optimization method called Simultaneous Aerodynamic Analysis and Design Optimization (SAADO) are extended from single discipline analysis (aerodynamics only) to multidisciplinary analysis - in this case, static aero-structural analysis - and applied to a simple 3-D wing problem. The method aims to reduce the computational expense incurred in performing shape optimization using state-of-the-art Computational Fluid Dynamics (CFD) flow analysis, Finite Element Method (FEM) structural analysis and sensitivity analysis tools. Results for this small problem show that the method reaches the same local optimum as conventional optimization. However, unlike its application to the win,, (single discipline analysis), the method. as I implemented here, may not show significant reduction in the computational cost. Similar reductions were seen in the two-design-variable (DV) problem results but not in the 8-DV results given here.
    Keywords: Aerodynamics
    Type: AIAA Paper 2001-1107 , Aerospace Sciences; Jan 08, 2001 - Jan 11, 2001; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Simultaneous Aerodynamic Analysis and Design Optimization (SAADO) for a 3-D Flexible Wing (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The formulation and implementation of an optimization method called Simultaneous Aerodynamic Analysis and Design Optimization (SAADO) are extended from single discipline analysis (aerodynamics only) to multidisciplinary analysis - in this case, static aero-structural analysis and applied to a simple 3-D wing problem. The method aims to reduce the computational expense incurred in performing shape optimization using state-of-the-art Computational Fluid Dynamics (CFD) flow analysis, Finite Element Method (FEM) structural analysis and sensitivity analysis tools. Results for this small problem show that the method reaches the same local optimum as conventional optimization. However, unlike its application to the rigid wing (single discipline analysis), the method, as implemented here, may not show significant reduction in the computational cost. Similar reductions were seen in the two-design-variable (DV) problem results but not in the 8-DV results given here.
    Keywords: Aerodynamics
    Type: AIAA Paper 2001-1107 , Aerospace Sciences; Jan 08, 2001 - Jan 11, 2001; Reno, NV; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Aerodynamic Analyses and Database Development for Lift-Off/Transition and First Stage Ascent of the Ares I A106 Vehicle (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA Langley Research Center, in partnership with NASA Marshall Space Flight Center and NASA Ames Research Center, was involved in the aerodynamic analyses, testing, and database development for the Ares I A106 crew launch vehicle in support of the Ares Design and Analysis Cycle. This paper discusses the development of lift-off/transition and ascent databases. The lift-off/transition database was developed using data from tests on a 1.75% scale model of the A106 configuration in the NASA Langley 14x22 Subsonic Wind Tunnel. The power-off ascent database was developed using test data on a 1% A106 scale model from two different facilities, the Boeing Polysonic Wind Tunnel and the NASA Langley Unitary Plan Wind Tunnel. The ascent database was adjusted for differences in wind tunnel and flight Reynolds numbers using USM3D CFD code. The aerodynamic jet interaction effects due to first stage roll control system were modeled using USM3D and OVERFLOW CFD codes.
    Keywords: Aerodynamics
    Type: NF1676L-11880 , 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition; Jan 04, 2011 - Jan 07, 2011; Orlando, FL; United States
    Format: application/pdf
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  • 4
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    A package for unstructured grid generation and finite element flow solvers (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A set of programs for unstructured mesh construction, fluid flow calculation and flow field visualization in two and three dimensions is described. The grid generators are based on the advancing front concept. The flow solvers use the finite element methods with Flux Corrected Transport techniques to solve several sets of equations including the Euler and Burger's equations. Several examples show the flexibility and accuracy of the methods.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 89-2175 , AIAA Applied Aerodynamics Conference; Jul 31, 1989 - Aug 02, 1989; Seattle, WA; United States
    Format: text
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  • 5
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    Simultaneous Aerodynamic and Structural Design Optimization (SASDO) for a 3-D Wing (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The formulation and implementation of an optimization method called Simultaneous Aerodynamic and Structural Design Optimization (SASDO) is shown as an extension of the Simultaneous Aerodynamic Analysis and Design Optimization (SAADO) method. It is extended by the inclusion of structure element sizing parameters as design variables and Finite Element Method (FEM) analysis responses as constraints. The method aims to reduce the computational expense. incurred in performing shape and sizing optimization using state-of-the-art Computational Fluid Dynamics (CFD) flow analysis, FEM structural analysis and sensitivity analysis tools. SASDO is applied to a simple. isolated, 3-D wing in inviscid flow. Results show that the method finds the saine local optimum as a conventional optimization method with some reduction in the computational cost and without significant modifications; to the analysis tools.
    Keywords: Aerodynamics
    Type: AIAA Paper 2001-2527 , 15th AIAA Computational Fluid Dynamics; Jun 11, 2001 - Jun 14, 2001; Anaheim, CA; United States
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  • 6
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    Multifidelity, Multidisciplinary Design Under Uncertainty with Non-Intrusive Polynomial Chaos (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The primary objective of this work is to develop an approach for multifidelity uncertainty quantification and to lay the framework for future design under uncertainty efforts. In this study, multifidelity is used to describe both the fidelity of the modeling of the physical systems, as well as the difference in the uncertainty in each of the models. For computational efficiency, a multifidelity surrogate modeling approach based on non-intrusive polynomial chaos using the point-collocation technique is developed for the treatment of both multifidelity modeling and multifidelity uncertainty modeling. Two stochastic model problems are used to demonstrate the developed methodologies: a transonic airfoil model and multidisciplinary aircraft analysis model. The results of both showed the multifidelity modeling approach was able to predict the output uncertainty predicted by the high-fidelity model as a significant reduction in computational cost.
    Keywords: Theoretical Mathematics; Statistics and Probability; Aerodynamics
    Type: NF1676L-24657 , 2017 AIAA SciTech Forum; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
    Format: application/pdf
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