Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints
In this study, the optimization of a low-speed wing with functional constraints is discussed. The aerodynamic analysis tool developed by the coupling of the numerical nonlinear lifting-line method to Xfoil is used to obtain lift and drag coefficients of the baseline wing. The outcomes are compared w...
Saved in:
| Main Authors: | , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
Wiley
2019-01-01
|
| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2019/3050824 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| _version_ | 1832552283334770688 |
|---|---|
| author | Durmuş Sinan Körpe Öztürk Özdemir Kanat |
| author_facet | Durmuş Sinan Körpe Öztürk Özdemir Kanat |
| author_sort | Durmuş Sinan Körpe |
| collection | DOAJ |
| description | In this study, the optimization of a low-speed wing with functional constraints is discussed. The aerodynamic analysis tool developed by the coupling of the numerical nonlinear lifting-line method to Xfoil is used to obtain lift and drag coefficients of the baseline wing. The outcomes are compared with the results of the solver based on the nonlinear lifting-line theory implemented into XLFR5 and the transition shear stress transport model implemented into ANSYS-Fluent. The agreement between the results at the low and moderate angle of attack values is observed. The sequential quadratic programming algorithm of the MATLAB optimization toolbox is used for the solution of the constrained optimization problems. Three different optimization problems are solved. In the first problem, the maximization of CL3/2/CD is the objective function, while level flight condition at maximum CL3/2/CD is defined as a constraint. The functional constraints related to the wing weight, the wing planform area, and the root bending moment are added to the first optimization problem, and the second optimization problem is constructed. The third optimization problem is obtained by adding the level flight condition and the available power constraints at the maximum speed and the level flight condition at the minimum speed of the baseline unmanned air vehicle to the second problem. It is demonstrated that defining the root bending moment, the wing area, and the available power constraints in the aerodynamic optimization problems leads to more realistic wing planform and airfoil shapes. |
| format | Article |
| id | doaj-art-33be8a85df7641eea310ae111ae9526a |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2019-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-33be8a85df7641eea310ae111ae9526a2025-02-03T05:58:59ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742019-01-01201910.1155/2019/30508243050824Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance ConstraintsDurmuş Sinan Körpe0Öztürk Özdemir Kanat1Aeronautical Engineering, University of Turkish Aeronautical Association, Ankara 06790, TurkeyDepartment of Airframe and Powerplant Maintenance, Kastamonu University, Kastamonu 37200, TurkeyIn this study, the optimization of a low-speed wing with functional constraints is discussed. The aerodynamic analysis tool developed by the coupling of the numerical nonlinear lifting-line method to Xfoil is used to obtain lift and drag coefficients of the baseline wing. The outcomes are compared with the results of the solver based on the nonlinear lifting-line theory implemented into XLFR5 and the transition shear stress transport model implemented into ANSYS-Fluent. The agreement between the results at the low and moderate angle of attack values is observed. The sequential quadratic programming algorithm of the MATLAB optimization toolbox is used for the solution of the constrained optimization problems. Three different optimization problems are solved. In the first problem, the maximization of CL3/2/CD is the objective function, while level flight condition at maximum CL3/2/CD is defined as a constraint. The functional constraints related to the wing weight, the wing planform area, and the root bending moment are added to the first optimization problem, and the second optimization problem is constructed. The third optimization problem is obtained by adding the level flight condition and the available power constraints at the maximum speed and the level flight condition at the minimum speed of the baseline unmanned air vehicle to the second problem. It is demonstrated that defining the root bending moment, the wing area, and the available power constraints in the aerodynamic optimization problems leads to more realistic wing planform and airfoil shapes.http://dx.doi.org/10.1155/2019/3050824 |
| spellingShingle | Durmuş Sinan Körpe Öztürk Özdemir Kanat Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints International Journal of Aerospace Engineering |
| title | Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints |
| title_full | Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints |
| title_fullStr | Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints |
| title_full_unstemmed | Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints |
| title_short | Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints |
| title_sort | aerodynamic optimization of a uav wing subject to weight geometric root bending moment and performance constraints |
| url | http://dx.doi.org/10.1155/2019/3050824 |
| work_keys_str_mv | AT durmussinankorpe aerodynamicoptimizationofauavwingsubjecttoweightgeometricrootbendingmomentandperformanceconstraints AT ozturkozdemirkanat aerodynamicoptimizationofauavwingsubjecttoweightgeometricrootbendingmomentandperformanceconstraints |