| Download | - View accepted manuscript: Boundary layer behaviour on a morphing airfoil: simulation and wind tunnel tests (PDF, 742 KB)
|
|---|
| Author | Search for: Sainmont, Corentin; Search for: Paraschivoiu, Ion; Search for: Coutu, Daniel; Search for: Brailovski, Vladimir; Search for: Laurendeau, Eric; Search for: Mamou, Mahmoud1; Search for: Mebarki, Youssef1; Search for: Khalid, Mahmood1 |
|---|
| Name affiliation | - National Research Council of Canada. NRC Institute for Aerospace Research
|
|---|
| Format | Text, Article |
|---|
| Proceedings title | Canadian Aeronautics and Space Institute AERO '09 Conference Aerodynamics Symposium [Proceedings] |
|---|
| Conference | Canadian Aeronautics and Space Institute AERO '09 Conference Aerodynamics Symposium, May 5-7, 2009, Kanata, Ontario |
|---|
| Abstract | This paper presents the boundary layer transitional flow behaviour past a morphing experimental wing. The objective of the present investigation is to reduce aerodynamic drag through laminar-turbulent transition location delay to promote large laminar region on the wing surface. The airfoil shape configurations of the adaptable part of the wing were optimized to extend the laminar flow on the upper surface of the airfoil. The optimizations were preformed with two different approaches. The classical approach uses a mathematical curve to model the flexible part. The multidisciplinary approach integrates the finite element model of the adaptable wing structure into the aerodynamic optimization process. The latter approach avoids the difficult task of reproducing the geometric representations of the airfoils, leading to the optimum performances offered by the morphing wing system. The optimizations are performed for various subsonic incompressible regimes using the computational fluid dynamics code Xfoil (Drela 2006) and the structural analysis software ANSYS coupled with a genetic optimization algorithm (Genial v1.1). Simulation and experimental results are presented and show that the morphing system is able to delay the transition location downstream by up to 30% of the chord length and to reduce the airfoil drag by up to 22%. Infra red maps and unsteady pressure frequency spectra measured on of the upper surface of the wing are also presented and show the laminar run extension. |
|---|
| Publication date | 2009 |
|---|
| Language | English |
|---|
| Peer reviewed | Yes |
|---|
| NRC publication | This is a non-NRC publication"Non-NRC publications" are publications authored by NRC employees prior to their employment by NRC. |
|---|
| NPARC number | 23001257 |
|---|
| Export citation | Export as RIS |
|---|
| Report a correction | Report a correction |
|---|
| Record identifier | 2c4c7828-10d2-465e-95be-467d03da751a |
|---|
| Record created | 2017-01-12 |
|---|
| Record modified | 2020-08-11 |
|---|
