publication . Article . 2017

NUMERICAL INVESTIGATION OF TWO ELEMENT CAMBER MORPHING AIRFOIL IN LOW REYNOLDS NUMBER FLOWS

RAJESH SENTHIL KUMAR T.; V. SIVAKUMAR; BALAJEE RAMAKRISHNANANDA; ARJHUN A.K, SURIYAPANDIYAN;
Open Access English
  • Published: 01 Jul 2017 Journal: Journal of Engineering Science and Technology (issn: 1823-4690, Copyright policy)
  • Publisher: Taylor's University
Abstract
Aerodynamic performance of a two-element camber morphing airfoil was investigated at low Reynolds number using the transient SST model in ANSYS FLUENT 14.0 and eN method in XFLR5. The two-element camber morphing concept was employed to morph the baseline airfoil into another airfoil by altering the orientation of mean-line at 35% of the chord to achieve better aerodynamic efficiency. NACA 0012 was selected as baseline airfoil. NACA 23012 was chosen as the test case as it has the camber-line similar to that of the morphed airfoil and as it has the same thickness as that of the baseline airfoil. The simulations were carried out at chord based Reynolds numbers of 2...
Subjects
free text keywords: Morphing airfoil, SUAV, CFD, Low Reynolds number flow; Aerodynamics., Low Reynolds number flow, Aerodynamics, Engineering (General). Civil engineering (General), TA1-2040, Technology (General), T1-995
32 references, page 1 of 3

1. Barbarino, S.;Bilgen, O.; Friswell, M.I.;Ajai, R.M.; and Inman, D.J. (2010). A review of morphing aircraft. Journal of Intelligent Material Systems and Structures, 22(9), 823-877.

2. Friswell, M.I. (2014). Morphingaircraft: an improbable dream? Proceedings of the ASME 2014 Conference on Smart Materials, Adaptive Structures and Intelligent Systems, Newport, Rhode Island, USA,1-7. [OpenAIRE]

Vasista, S.;Tong, L.; and Wong, K.C. (2012). Realization of morphing wings: amultidisciplinary challenge. Journal of Aircraft, 49(1), 11-28.

4. Poonsong, P. (2004). Design and analysis of a multi-section variable camber wing. MSc. Thesis. University of Maryland, College Park, MD 20742, United States.

Ko, S.H.;Bae, J.S.;and Rho, J.H. (2014). Development of a morphing flap using shape memory alloy actuators: the aerodynamic characteristics of a morphing flap. Smart Materials and Structures, 23(7), 1-21.

Wang, Y. (2015). Development of flexible-rib morphing wing system. M.Sc.

Thesis. University of Toronto, 27 King's College Cir, ON M5S, Canada.

Woods, B.K.S.; Bilgen, O.; and Friswell, M.I. (2014). Wind tunnel testing of the fish bone active camber morphing concept. Journal of Intelligent Material Systems and Structures, 25(7),772-785. [OpenAIRE]

8. Counsil, J.N.N.; and Boulama, K.G. (2013). Low-Reynolds-number aerodynamic performance of NACA 0012 and Selig-Donovan 7003 airfoils. Journal of Aircraft, 50(1), 204-216.

XFLR5 ver. 6.10.04 (2014).

fromhttp://www.xflr5.com/xflr5.htm

10. Selig, M.S.; Deters, R.W.; and Williamson, G.A. (201l). Wind tunnel testing airfoils at low reynolds numbers. 49th AIAA Aerospace Sciences Meeting, Orlando, FL, 1-32.

11. Van Ingen, J.L. (2008). The eN method for transition prediction. Historical review of work at TU Delft. 38thFluid Dynamics Conference and Exhibit, Seattle, Washington, 1-49.

12. Wahidi, R.; and Bridges, D.H. (2009). Experimental investigation of the boundary layer and pressure measurements on airfoil with laminar separation bubbles. 39th AIAA Fluid Dynamics Conference, San Antonia, Texas. [OpenAIRE]

13. Muller, T.J. (1999). Aerodynamic measurements at low Reynolds numbers for fixed wing micro aerial vehicles. University of Notre Dame, Notre Dame, IN46556, USA, 1-32.

32 references, page 1 of 3
Abstract
Aerodynamic performance of a two-element camber morphing airfoil was investigated at low Reynolds number using the transient SST model in ANSYS FLUENT 14.0 and eN method in XFLR5. The two-element camber morphing concept was employed to morph the baseline airfoil into another airfoil by altering the orientation of mean-line at 35% of the chord to achieve better aerodynamic efficiency. NACA 0012 was selected as baseline airfoil. NACA 23012 was chosen as the test case as it has the camber-line similar to that of the morphed airfoil and as it has the same thickness as that of the baseline airfoil. The simulations were carried out at chord based Reynolds numbers of 2...
Subjects
free text keywords: Morphing airfoil, SUAV, CFD, Low Reynolds number flow; Aerodynamics., Low Reynolds number flow, Aerodynamics, Engineering (General). Civil engineering (General), TA1-2040, Technology (General), T1-995
32 references, page 1 of 3

1. Barbarino, S.;Bilgen, O.; Friswell, M.I.;Ajai, R.M.; and Inman, D.J. (2010). A review of morphing aircraft. Journal of Intelligent Material Systems and Structures, 22(9), 823-877.

2. Friswell, M.I. (2014). Morphingaircraft: an improbable dream? Proceedings of the ASME 2014 Conference on Smart Materials, Adaptive Structures and Intelligent Systems, Newport, Rhode Island, USA,1-7. [OpenAIRE]

Vasista, S.;Tong, L.; and Wong, K.C. (2012). Realization of morphing wings: amultidisciplinary challenge. Journal of Aircraft, 49(1), 11-28.

4. Poonsong, P. (2004). Design and analysis of a multi-section variable camber wing. MSc. Thesis. University of Maryland, College Park, MD 20742, United States.

Ko, S.H.;Bae, J.S.;and Rho, J.H. (2014). Development of a morphing flap using shape memory alloy actuators: the aerodynamic characteristics of a morphing flap. Smart Materials and Structures, 23(7), 1-21.

Wang, Y. (2015). Development of flexible-rib morphing wing system. M.Sc.

Thesis. University of Toronto, 27 King's College Cir, ON M5S, Canada.

Woods, B.K.S.; Bilgen, O.; and Friswell, M.I. (2014). Wind tunnel testing of the fish bone active camber morphing concept. Journal of Intelligent Material Systems and Structures, 25(7),772-785. [OpenAIRE]

8. Counsil, J.N.N.; and Boulama, K.G. (2013). Low-Reynolds-number aerodynamic performance of NACA 0012 and Selig-Donovan 7003 airfoils. Journal of Aircraft, 50(1), 204-216.

XFLR5 ver. 6.10.04 (2014).

fromhttp://www.xflr5.com/xflr5.htm

10. Selig, M.S.; Deters, R.W.; and Williamson, G.A. (201l). Wind tunnel testing airfoils at low reynolds numbers. 49th AIAA Aerospace Sciences Meeting, Orlando, FL, 1-32.

11. Van Ingen, J.L. (2008). The eN method for transition prediction. Historical review of work at TU Delft. 38thFluid Dynamics Conference and Exhibit, Seattle, Washington, 1-49.

12. Wahidi, R.; and Bridges, D.H. (2009). Experimental investigation of the boundary layer and pressure measurements on airfoil with laminar separation bubbles. 39th AIAA Fluid Dynamics Conference, San Antonia, Texas. [OpenAIRE]

13. Muller, T.J. (1999). Aerodynamic measurements at low Reynolds numbers for fixed wing micro aerial vehicles. University of Notre Dame, Notre Dame, IN46556, USA, 1-32.

32 references, page 1 of 3
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