Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Efficiency improvement in sensitivity evaluation in aerodynamic shape optimization
Date
1996-01-01
Author
Eyi, Sinan
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
140
views
0
downloads
Cite This
© 1996 by the American Institute of Aeronautics and Astronautics, Inc. All rights resewed.The paper presents two methods that improve the accuracy and reduce the computational cost in evaluating finite-difference sensitivities for aerodynamic shape optimization. The first method is a modified finite-difference approach that improves the accuracy of sensitivities at a reduced cost using an improved iteration strategy. The second method finds the optimum perturbation size based on an asymptotic error formula. These two methods were implemented and demonstrated for inverse design optimizations, exhibiting consistently better performance compared to traditional finite-difference methods.
URI
https://hdl.handle.net/11511/69350
DOI
https://doi.org/10.2514/6.1996-2506
Collections
Department of Aerospace Engineering, Conference / Seminar
Suggestions
OpenMETU
Core
Numerical investigation of subsonic flow over a typical missile forebody
Tuncer, İsmail Hakkı; Platzer, Max F. (1996-01-01)
© 1996, American Institute of Aeronautics and Astronautics, Inc. All Rights Reserved.The NASA-Ames developed Navier-Stokes solver OVERFLOW and the panel code PMARC are applied to the computation of the flow over a typical missile forebody. The flowfields at low angles of attack from 0° to 14° are investigated. The surface pressures along the missile forebody predicted by OVERFLOW and PMARC agree well up to 10°. This favorable agreement suggests that the panel codes may be a computationally efficient tool fo...
Noise prediction of a transonic cavity flow via shear-layer-adapted delayed detached-eddy simulation
Yalçın, Özgür; Özyörük, Yusuf (2018-01-01)
© 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.An open cavity flow contains a highly turbulent shear layer which separates from the upstream edge and impinges on the aft wall of the cavity, causing intense noise emission. In this study, a delayed detached-eddy simulation (DDES) with the use of "shear-layer-adapted" subgrid length scale, an enhancement of DDES available in literature, is conducted for such an open cavity flow problem. The results show that this len...
Analysis of unsteady airfoil interference effects using a zonal Navier-Stokes solver
Tuncer, İsmail Hakkı (null; 1995-01-01)
© 1995, by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.Unsteady aerodynamic interference effects and thrust generation on a flapping/stationary airfoil combination in tandem are studied parametrically. A zonal Navier-Stokes solver is employed to compute the unsteady flowfield. The computational domain is discretized with overlapping uniform grids generated around each airfoil. The thrust generation and the propulsive efficiency of the flapping/stationary airfoil combinat...
Analysis and design optimization of three dimensional nozzles
Yildizlar, B.; Eyi, Sinan (2014-01-01)
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The aim of this study is to develop analysis and design optimization method for three dimensional nozzles. For analysis, three dimensional Euler equations are solved using both Newton and Newton-GMRES methods and their performances are compared. The Jacobian matrix needed for Newton method is evaluated analytically. Newton-GMRES method is a matrix free solution technique hence it does not require the Jacobian matrix e...
Static aeroelastic analysis of supersonic nozzles and performance response
Duzel, U.; Eyi, Sinan (2014-01-01)
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The effects of static aeroelasticity on the performance of supersonic nozzles are analyzed. A flow analysis was conducted to investigate five different configurations of two dimensional convergingdiverging nozzles. Computational results are validated with experimental data. Two of the configurations, which have the same throat area, throat radius, and convergence angle and total nozzle length are selected as the basel...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
S. Eyi, “Efficiency improvement in sensitivity evaluation in aerodynamic shape optimization,” 1996, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69350.