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
Aerodynamic optimization of wing-body configuration using discrete adjoint method
Date
2017-01-01
Author
Yıldırım, Ahmet
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
260
views
0
downloads
Cite This
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.The gradient based sensitivities required by design optimization are obtained by three different methods based on three dimensional Euler equations. Finite difference, Direct and Adjoint methods are used to compute objective sensitivities. A cell centered, upwind based finite volume method is implemented to discretize the Euler equations. The flow solution is obtained by preconditioned matrix-free Newton-GMRES algorithm. The required derivatives for Adjoint and Direct methods are obtained by analytical derivation of discrete flow equations. Resulted linear systems are solved by PARDISO solver. Design variables are selected as Non-Uniform Rational B-Spline (NURBS) curve and surface control points while Radial Basis Function (RBF) is used in volume mesh deformation.
URI
https://hdl.handle.net/11511/69458
DOI
https://doi.org/10.2514/6.2017-3262
Collections
Department of Aerospace Engineering, Conference / Seminar
Suggestions
OpenMETU
Core
Aerodynamic parameter estimation of a supersonic air to air missile with rapid speed variation
Bayoglu, Tugba; Nalci, Mehmet Ozan; Kutay, Ali Türker (2016-01-01)
© 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.Maneuver inputs designed for aircraft parameter identification are often applied during the aircraft flies close to a trimmed flight condition at an approximately constant Mach number. Since a fixed wing aircraft has control over its thrust and speed, various maneuver inputs can be applied to identify aerodynamic derivatives at discrete Mach numbers. On the contrary, most agile missile configurations do not have contr...
Modification of the extended messinger model for mixed phase icing and industrial applications with TAICE
Ayan, Erdem; Özgen, Serkan (2017-01-01)
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Computational studies have been performed in order to predict mixed phase ice accretion on aircraft components. In-house developed TAICE tool has been used in this study. Previously, TAICE was already validated for icing cases due to water droplets only. In addition, in the framework of High Altitude Ice Crystals (HAIC) FP7 European project, mixed phase ice accretion prediction capability has been added to TAICE. Up to...
Experimental design and statistical modeling methodology for wind tunnel aerodynamics of an agile missile to improve the simulation accuracy and performance
Savas, Ozgun; Topbas, Eren; Unal, Kenan; Karaca, H. Deniz; Kutay, Ali Türker (2018-01-01)
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Wind tunnel testing is an essential procedure to investigate the aerodynamics forces and moments. In this paper, a methodology is presented to perform such test in an efficient way. Experimental design process is carried out before the testing in order to cover the flight regime as much as possible with the least possible number of tests. After the determination of the test matrix and conducting the wind-on tests, the ...
Analysis of effects of different diffusion models in hypersonic flow regimes
Gur, H. Berk; Eyi, Sinan (2017-01-01)
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Hypersonic flows become popular due to its use in space explorations and military applications. It occurs normally, when a space craft re-enter to the atmosphere. Space crafts are exposed to high temperatures and high pressures because of Earth’s atmosphere and gravity. In addition in high temperatures, gases tend to react with each other. These reactions also have effects on space craft’s surface. In order to calculat...
Aeroelastic Model Corrections of a Very Light Aircraft; Implications on Static Trim, Flutter and Gust Response
Demirer, Halime Gül; Kayran, Altan (2022-01-01)
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.This paper discusses the aeroelastic model corrections employed in the static and dynamic aeroelastic analysis of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. Discussion covers improvement of the aerodynamic solution, aerodynamic modeling approaches and aero-structure coupling alternatives. Aerodynamic calculations are based on the Doublet-Lattice Method (DLM). ...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
A. Yıldırım and S. Eyi, “Aerodynamic optimization of wing-body configuration using discrete adjoint method,” 2017, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69458.
