# Automation of Winglet Wings Geometry Generation for Its Application in TORNADO
## 2 Methods
### Definition of the Wingtip Devices
#### 2.2.2 Open and Closed Spiroid Winglet
Available online: [[http://web.mit.edu/drela/Public/web/avl/](http://web.mit.edu/drela/Public/web/avl/)]([http://web.mit.edu/drela/Public/web/avl/](http://web.mit.edu/drela/Public/web/avl/)) (accessed on 22 August 2023). * (7)_Surfaces--Vortex-Lattice Module_ ; Great OWL Publishing: Ephrata, PA, USA, 2009
* (8) Official Website of VSPAERO. Available online: [[https://openvsp.org/wiki/doku.php?id=vspaerotutorial](https://openvsp.org/wiki/doku.php?id=vspaerotutorial)]([https://openvsp.org/wiki/doku.php?id=vspaerotutorial](https://openvsp.org/wiki/doku.php?id=vspaerotutorial)) (accessed on 22 August 2023 ). * (9) [PERSON]; [PERSON]; [PERSON] A new non-linear Vortex Lattice Method: Applications to wing aerodynamic optimizations. _[PERSON]. J. Aeronaut._**2016**, _29_, 1178-1195. [CrossRef]
* (10) [PERSON]; [PERSON]; [PERSON] Experimental and Nonlinear Vortex Lattice Method Results for Various Wing-Canard Configurations. _J. Aircr._**1993**, _30_, 207-212. [CrossRef]
* (11) [PERSON]; [PERSON] Review of vortex lattice method for supersonic aircraft design. _Aeronaut. J._**2023**, 1-35. [CrossRef]
* (12) [PERSON] _User's Guide and Reference Manual for Tornado_; Royal Institute of Technology (KTH): Stockholm, Sweden, 2000. * (13) [PERSON] Drag due to lift: Concepts for prediction and reduction. _Annu. Rev. Fluid Mech._**2001**, _33_, 587-617. [CrossRef]
* (14) [PERSON] Wing aerodynamics and the science of compromise. _Aeronaut. J._**2001**, _105_, 633-641. [CrossRef]
* (15) [PERSON]; Langley Research Center and United States. _A Design Approach and Selected Wind Tunnel Results at High Subsonic Speeds for Wing-Tip Mounted Winglets_; National Aeronautics and Space Administration: Washington, DC, USA, 1976. * (16) [PERSON]; [PERSON] Winglets on low-aspect-ratio wings. _J. Aircr._**1988**, _25_, 932-941. [CrossRef]
* (17) [PERSON]. Blended Winglet. U.S. Patent 5,348,253, 20 September 1994. * (18) [PERSON]. Spiroid-Tipped Wing. U.S. Patent 5,102,06, 7 April 1992. * (19) [PERSON]; [PERSON]; [PERSON] Experimental study of vortex shapes behind a wing equipped with different winglets. _J. Aerosp. Sci. Technol._**2006**, \(3\), 1-20. * (20) [PERSON]; [PERSON] Aerodynamic efficiency study of modern spiroid winglets. _J. Aeronaut. Astronaut. Aviat._**2009**, _41_, 23-29. * (21) [PERSON]; [PERSON]; [PERSON]; [PERSON] Commercial aircraft performance improvement using winglets. _FME Trans._**2015**, _43_, 1-8. [CrossRef]
* (22) [PERSON]; [PERSON]; [PERSON]; [PERSON]; [PERSON]; [PERSON]; [PERSON] A parametric investigation of non-circular spiperiod winglets. _EPJ Web Conf._**2014**, _67_, 02077. [CrossRef]
* (23) [PERSON]; [PERSON]; [PERSON] Biomimetic spiroid winglets for lift and drag control. _Comptes Rendus Mec._**2012**, _340_, 67-80. [CrossRef]
* (24) [PERSON], [PERSON] Wing with a Wing Grid as the End Section. U.S. Patent 5,823,480, 20 October 1998. * (25) [PERSON] [PERSON]; [PERSON] Induced drag reduction using multiple winglets, looking beyond the prandtl-munk linear model. In Proceedings of the 2 nd AIAA Flow Control Conference, Portland, OR, USA, 28 June-1 July 2004; p. 2120. * (26) [PERSON]; [PERSON]; [PERSON]; [PERSON]; [PERSON] Active multiple winglets for improved unmanned-aerial-vehicle performance. _J. Aircr._**2006**, _43_, 110-116. * (27) [PERSON]; [PERSON]; [PERSON] _The Wing Grid: A New Approach to Reducing Induced Drag_; Massachusetts Institute of Technology: Cambridge, MA, USA, 2001. * (28) [PERSON]; [PERSON]; [PERSON] _Blended Winglets_; Aero, Boeing: Arlington, VR, USA, 2002. * (29) [PERSON] Linear Strength Vortex Panel Method for NACA 4412 Airfoil. _IOP Conf. Ser. Mater. Sci. Eng._**2018**, _326_, 012016. [CrossRef]

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