Surface mesh of the TUDELFT_V3_KITE CAD with edge fillets.

A surface mesh representing the TUDELFT_V3_KITE at true scale is present. Unlike the real kite, edge fillets are added, the trailing edge connecting the upper and lower surfaces is rounded and no bridle lines are present.It was initially developed in 2022 for aerodynamic CFD simulations, and used in a MSc Thesis by G. Lebesque titled: Steady-state RANS simulation of a leading edge inflatable wing with chordwise struts. This work was published as: Viré A., Lebesque G., Folkersma M., Schmehl R. (2022) Effect of Chordwise Struts and Misaligned Flow on the Aerodynamic Performance of a Leading-Edge Inflatable Wing. Energies 15(4): 1450. https://doi.org/10.3390/en15041450 The current file is no longer identical to the one used for CFD simulations in the paper mentioned above, but has been rotated, translated, and axis transformed. To adhere to the paper: Poland, J. A. W., van Spronsen, J. M., Mac Gaunaa, & Schmehl, R. (2025). Wind tunnel load measurements of a leading‐edge inflatable kite rigid scale model. Wind Energy Science. (add doi)Rotation was done by pitching the wing at an angle of 1.02°, such that the mid-span chord line (used to define the angle of attack) was parallel to the horizontal plane. Translation has been done to set the leading-edge point at mid-span at the origin. Finally, the axis transformation has been applied to adhere to the definition employed by the Vortex-Step Method, and the wind tunnel experiment. The new axis has the x-axis defined from the leading edge to the trailing edge, parallel to the mid-span chord line. The y-axis is described in the spanwise direction to the left, when looking from the front (in the positive x direction). The z-axis is defined upwards, when looking from the front (in the positive x direction).This research has been supported by the Nederlandse Organisatie voor Wetenschappelijk Onderzoek (NWO) under grant number 17628.存在一个按真实比例构建的TUDELFT_V3_KITE表面网格（surface mesh）。与真实风筝不同，该网格添加了边缘圆角（edge fillets），连接上下翼面的后缘做了圆角处理，且未设置牵绳（bridle lines）。 该模型最初于2022年开发，用于空气动力学计算流体动力学（Computational Fluid Dynamics, CFD）仿真，并被G. Lebesque用于其硕士论文《带弦向支柱的前缘充气翼的定常雷诺平均纳维-斯托克斯（Reynolds-Averaged Navier-Stokes, RANS）仿真》。该研究成果已发表为：Viré A.、Lebesque G.、Folkersma M.、Schmehl R. (2022) 《弦向支柱与流场失准对前缘充气翼气动性能的影响》，*Energies*，15(4): 1450。https://doi.org/10.3390/en15041450 当前文件已与上述论文中用于CFD仿真的原始文件不再完全一致，而是经过了旋转、平移与坐标轴变换。为符合论文：Poland, J. A. W.、van Spronsen, J. M.、Mac Gaunaa、Schmehl, R. (2025) 《风洞缩比刚性前缘充气风筝载荷测量》，*Wind Energy Science*（需补充DOI）。 旋转操作通过将机翼俯仰1.02°完成，使用于定义攻角的展中弦线与水平面平行。平移操作将展中位置的前缘点设置为坐标原点。最后，为符合涡旋步进法（Vortex-Step Method）与风洞实验的坐标轴定义，对坐标系进行了变换。新坐标系的x轴由前缘指向后缘，与展中弦线平行；从前方沿x轴正方向观察时，y轴沿展向向左为正方向；从前方沿x轴正方向观察时，z轴向上为正方向。 本研究得到荷兰科学研究组织（Nederlandse Organisatie voor Wetenschappelijk Onderzoek, NWO）资助，项目编号为17628。