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Aerodynamics of Discrete Location Camber Morphing Airfoils in Low Reynolds Number Flows
Objectives: This paper focuses on morphing the base airfoil similar into that of the target airfoil for the application of small unmanned aerial vehicle in low Reynolds number regime. Methods/Statistical Analysis: In this study, discrete location camber morphing approach was used to achieve the morphing configurations of base airfoil. Discrete location camber morphing method was classified into single, two and three location morphing configuration based on the number of morphing locations. The aerodynamic performance of morphed airfoil configurations were studied at the low Reynolds numbers of 2.5 × 105 and 3.9 × 105 using XFLR5 - eN method. Findings: The base airfoil for this study was selected as NACA0012. The E 207 airfoil which has better aerodynamic performance in low Reynolds number regime was selected as the target airfoil. Eleven different morphing configurations of base airfoil were developed for this study, which falls under these three classifications. Two out of eleven morphed configurations have similar geometric features and equivalent performance as that of E 207 for different range of angles of attack. These two morphed configurations showed a rise of about 3% in maximum aerodynamic efficiency compared to the target airfoil for the tested Reynolds number. Out of these two morphed configurations, one belongs to two location morphing method and another belongs to three location morphing method. This study also reveals that atleast one morphing location has to be closer to maximum camber position of the target airfoil to achieve an effective morphing. There is a possibility for switching between these two morphed configurations as they have two common morphing locations during the flight. Application/Improvements: This type of camber morphing can be positively applied in small unmanned aerial vehicles to achieve better aerodynamic performance over the entire flight mission.
Aerodynamics, Discrete Location Camber Morphing, Low Reynolds Number Flows, Morphing Airfoil, XFLR5.
- Barbarino S, Bilgen O, Ajaj R, Friswell M, Inman D. A Review of Morphing Aircraft. Journal of Intelligent Material Systems and Structures. 2011; 22(9):823–77. Crossref
- Friswell M. Morphing Aircraft. An Improbable Dream, Development and Characterization of Multifunctional Materials, Modeling, Simulation and Control of Adaptive Systems, Structural Health Monitoring. Keynote Presentation. 2014. PMCid:PMC3966804
- Vasista S, Tong L, Wong K. Realization of Morphing Wings: A Multidisciplinary Challenge. Journal of Aircraft. 2012; 49(1):11–28. Crossref
- Fincham JHS, Friswell MI. Aerodynamic optimization of Camber morphing aerofoil. Aerosapce Science and Technology. 2015; 43:245–55. Crossref
- Poonsong P. Design and Analysis of a Multi-Section variable camber Wing. [MSc. Thesis]. University of Maryland, College Park, United States. 2004.
- Ko S, Bae J, Rho J. Development of a morphing flap using shape memory alloy actuators: the aerodynamic characteristics of a morphing flap. Smart Materials and Structures. 2014; 23(7). Crossref
- Wang Y. Development of Flexible-Rib Morphing Wing system. [M.Sc. Thesis]. University of Toronto, Canada. 2015.
- Woods B, Bilgen O, Friswell M. Wind Tunnel Testing of the Fish Bone Active Camber Morphing Concept. Journal of Intelligent Material Systems and Structures. 2014; 25(7). Crossref
- Selig M, Deters R, Williamson G. Wind Tunnel Testing Airfoils at Low Reynolds Numbers. 49th AIAA Aerospace Sciences Meeting. Orlando. 2011. Crossref
- Van Ingen J L. The eN method for transition prediction. Historical review of work at TU Delft. 38th Fluid Dynamics Conference and Exhibit. Seattle. 2008. Crossref
- XFLR5.Analysis of Foils and Wings at Low Reynolds Numbers. Guidelines for XFLR5 ver. 6.10.04. Available from: Crossref
- Counsil J, Boulama KG. Low-Reynolds-Number Aerodynamic Performances of the NACA 0012 and Selig–Donovan 7003 Airfoils. Journal of Aircraft. 2013; 50(1):204–16. Crossref
- Niveditta T. An Efficient Image Quality Criterion in Spatial Domain. Indian Journal of Science and Technology. 2016; 9(34):1–6. Crossref
- Gulshan K, Praveen P, Rahul S, Kumar RM. Chaotic Image Encryption Technique based on IDEA and Discrete Wavelet Transformation. Indian Journal of Science and Technology. 2016 Apr; 9(15):1–6. Crossref
- Vimala C, Priya PA. Degraded Image Enhancement through Double Density Dual Tree Discrete Wavelet Transform. Indian Journal of Science and Technology. 2016 Jul; 9(28):1–4. Crossref
- Selig M, Donovan F. Airfoils at Low speeds. H.A. Stokely Publishers Meeting. Virginia, USA.1989.
- Williamson G, McGranahan B, Broughton B, Deters R, Selig M. Summary of Low Speed Airfoil Data-Volume 5. University of Illinois, Urbana-Champaign, USA. 2012.
- Hansen KL, Kelso RM, Choudhry A. Laminar Separation Bubble Effect on the Lift Curve Slope of an Airfoil. 19th Australasian Fluid Mechanics Conference. Melbourne, Australia. 2014.
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