Computational Simulation of the Flow Past an Airfoil for an Unmanned Aerial Vehicle
This paper deals with the numerical simulation of the two-dimensional, incompressible, steady air flow past a NACA 2415 airfoil and four modifications of this one. The modification of this airfoil was made in order to create a blowing outlet with the shape of a step on the suction surface. Therefore...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
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International Institute of Informatics and Cybernetics
2013-08-01
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| Series: | Journal of Systemics, Cybernetics and Informatics |
| Subjects: | |
| Online Access: | http://www.iiisci.org/Journal/CV$/sci/pdfs/iFA091MU.pdf
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| _version_ | 1811227509998485504 |
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| author | L. Velázquez-Araque J. Nožička |
| author_facet | L. Velázquez-Araque J. Nožička |
| author_sort | L. Velázquez-Araque |
| collection | DOAJ |
| description | This paper deals with the numerical simulation of the two-dimensional, incompressible, steady air flow past a NACA 2415 airfoil and four modifications of this one. The modification of this airfoil was made in order to create a blowing outlet with the shape of a step on the suction surface. Therefore, five different locations along the cord line for this blowing outlet were analyzed. This analysis involved the aerodynamic performance which meant obtaining lift, drag and pitching moment coefficients curves as a function of the angle of attack for the situation where the engine of the aerial vehicle is turned off called the no blowing condition by means computational fluid dynamics. The RNG k-ε model is utilized to describe the turbulent flow process. The simulations were held at a Reynolds number of 105. Results allowed obtaining lift and drag forces and pitching moment coefficient and also the location of the separation and reattachment point in some cases for different angles of attack, from 0 to 16 degrees with the smallest increment of 4 degrees. Finally, numerical results were compared with results obtained from wind tunnel tests by means of an aerodynamic balance and also oil and smoke visualization techniques and found to be in very good agreement. |
| first_indexed | 2024-04-12T09:43:31Z |
| format | Article |
| id | doaj.art-b890ca223a0f451fb2cf010d62e757ed |
| institution | Directory Open Access Journal |
| issn | 1690-4524 |
| language | English |
| last_indexed | 2024-04-12T09:43:31Z |
| publishDate | 2013-08-01 |
| publisher | International Institute of Informatics and Cybernetics |
| record_format | Article |
| series | Journal of Systemics, Cybernetics and Informatics |
| spelling | doaj.art-b890ca223a0f451fb2cf010d62e757ed2022-12-22T03:38:01ZengInternational Institute of Informatics and CyberneticsJournal of Systemics, Cybernetics and Informatics1690-45242013-08-011164046Computational Simulation of the Flow Past an Airfoil for an Unmanned Aerial VehicleL. Velázquez-Araque0J. Nožička1 Universidad Nacional Experimental del Táchira Czech Technical University in Prague This paper deals with the numerical simulation of the two-dimensional, incompressible, steady air flow past a NACA 2415 airfoil and four modifications of this one. The modification of this airfoil was made in order to create a blowing outlet with the shape of a step on the suction surface. Therefore, five different locations along the cord line for this blowing outlet were analyzed. This analysis involved the aerodynamic performance which meant obtaining lift, drag and pitching moment coefficients curves as a function of the angle of attack for the situation where the engine of the aerial vehicle is turned off called the no blowing condition by means computational fluid dynamics. The RNG k-ε model is utilized to describe the turbulent flow process. The simulations were held at a Reynolds number of 105. Results allowed obtaining lift and drag forces and pitching moment coefficient and also the location of the separation and reattachment point in some cases for different angles of attack, from 0 to 16 degrees with the smallest increment of 4 degrees. Finally, numerical results were compared with results obtained from wind tunnel tests by means of an aerodynamic balance and also oil and smoke visualization techniques and found to be in very good agreement.http://www.iiisci.org/Journal/CV$/sci/pdfs/iFA091MU.pdf None |
| spellingShingle | L. Velázquez-Araque J. Nožička Computational Simulation of the Flow Past an Airfoil for an Unmanned Aerial Vehicle Journal of Systemics, Cybernetics and Informatics None |
| title | Computational Simulation of the Flow Past an Airfoil for an Unmanned Aerial Vehicle |
| title_full | Computational Simulation of the Flow Past an Airfoil for an Unmanned Aerial Vehicle |
| title_fullStr | Computational Simulation of the Flow Past an Airfoil for an Unmanned Aerial Vehicle |
| title_full_unstemmed | Computational Simulation of the Flow Past an Airfoil for an Unmanned Aerial Vehicle |
| title_short | Computational Simulation of the Flow Past an Airfoil for an Unmanned Aerial Vehicle |
| title_sort | computational simulation of the flow past an airfoil for an unmanned aerial vehicle |
| topic | None |
| url | http://www.iiisci.org/Journal/CV$/sci/pdfs/iFA091MU.pdf
|
| work_keys_str_mv | AT lvelazquezaraque computationalsimulationoftheflowpastanairfoilforanunmannedaerialvehicle AT jnozicka computationalsimulationoftheflowpastanairfoilforanunmannedaerialvehicle |