4 edition of Efficient gradient-based shape optimization methodology using inviscid/viscous CFD found in the catalog.
Efficient gradient-based shape optimization methodology using inviscid/viscous CFD
by Dept. of Aerospace Engineering, College of Engineering and Technology, Old Dominion University, National Aeronautics and Space Administration, National Technical Information Service, distributor in Norfolk, Va, [Washington, DC, Springfield, Va
Written in English
|Other titles||Efficient gradient based shape optimization methodology using inviscid viscous CFD.|
|Statement||by Oktay Baysal, principal investigator ; submitted by the Old Dominion University Research Foundation.|
|Series||[NASA contractor report] -- NASA-CR-204385., NASA contractor report -- NASA CR-204385.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
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Efficient Gradient-Based Shape Optimization Methodology Using Inviscid/Viscous CFD Item Preview ) was the extension of the shape optimization methodology for the Thin-Layer Navier-Stokes equations.
Both the Euler-based and the TLNS-based analyses compared with the analyses obtained using the CFL3D code. The sensitivities, again from. Efficient gradient-based shape optimization methodology using inviscid/viscous CFD summary of research report for the period of March 9, to March 8,grant# NCC (SuDoc NAS ) [Oktay Baysal] on *FREE* shipping on qualifying offers.
Get this from a library. Efficient gradient-based shape optimization methodology using inviscid/viscous CFD: summary of research report for the period of March 9, to March 8,grant# NCC [Oktay Baysal; United States.
National Aeronautics and Space Administration.]. Buy Efficient gradient-based shape optimization methodology using inviscid/viscous CFD summary of research report for the period of March 9, to March 8,grant# NCC (SuDoc NAS ) by Oktay Baysal (ISBN:) from Amazon's Book Store.
Everyday low prices and free delivery on eligible : Oktay Baysal. Aerodynamic shape optimization of a helicopter rotor in hover is presented, using compressible CFD as the aerodynamic model.
An efficient domain element shape parameterization method is used as. A modular, generic optimization scheme is applied to CFD-based shape optimization of helicopter rotors in hovering flight.
An efficient domain element shape parameterization method is linked to a. Introduction. Organic Rankine Cycle (ORC) power systems are nowadays a mature and cost-effective technology for the efficient exploitation of energy sources characterized by low-to-medium temperature levels (Colonna et al., ).For source temperature levels below °C (Colonna and et al,Gaia, ), the adoption of molecularly complex and heavy organic fluids instead of steam Cited by: 5.
This work covers a contribution to two most interesting research fields in aerodynamics, the finite element analysis of high-speed compressible flows (Part I) and aerodynamic shape optimization (Part II).The first part of this study aims at the development of a new stabilization formulation based on the Finite Increment Calculus (FIC) scheme for the Euler and Navier-Stokes equations in the Author: M.
Kouhi, E. Oñate, G. Bugeda. Full text of "Aerodynamic shape optimization using control theory" See other formats. Initially, linear CFD methods were used, but in the last 5–10 years, Euler, coupled inviscid-viscous, and even Navier–Stokes methods are being used in the optimization process.
Different strategies exist in aerodynamic shape optimization as for example adjoint gradient methods , automatic differentiation techniques , heuristic Cited by: Using tensor mathematics, it can be shown that this problem entails solving the equations.
Orthogonality Adjustment Algorithm In several computational fluid dynamics applications, an orthogonal mesh is necessary in certain regions to ensure a. turbomachinery design. Journal of Mechanical Engineering Science, IMechE Proc. Part C, Vol. 21 3, No. C2, pp.ISSN: 0 Denton, J. ( Airfoil Shape Optimization based on Surrogate Model.
NASA Astrophysics Data System (ADS) Mukesh, R.; Lingadurai, K.; Selvakumar, U. Engineering design problems always.
Optimization with artificial neural network systems - A mapping principle and a comparison to gradient based methods. NASA Technical Reports Server (NTRS) Leong, Harrison Monfook. This banner text can have markup. web; books; video; audio; software; images; Toggle navigation.
This book covers a broad spectrum of chapters spanning the entire gas turbine and aerospace industry- from advances in engine design and characterization for engineering design, high temperature corrosion, design and development of smart protective coatings to provide total protection, turbine monitoring, diagnostics, various types of gas turbines, life prediction modeling and ﬁ nally 3/5(2).
Turbomachinary Aero Dynamics. Журнал International Journal of Heat and Fluid Flow PDF ENG. The motivation of this project is to solve large-scale shape optimization problems that arise in the aeronautics industry when searching for the shape that provides the best aerodynamic performance.
The approach combines gradient-based algorithms for the optimization and adjoint flow equations for the calculation of the gradients. Köller et al., and Küsters et al., developed a new family of compressor airfoils, characterized by low total pressure losses and larger operating range with respect to standard Controlled Diffusion Airfoils (CDA), using a gradient optimization method and an inviscid/viscous code.
Sixth IUTAM Symposium on Laminar-Turbulent Transition FLUID MECHANICS AND ITS APPLICATIONSVolume 78 Series Editor.International Journal of Heat and Fluid Flow!
Год выпуска: Жанр: Физика/Механика Издательство: ISSN: X.