AERODYNAMIC AND EXPERIMENTAL INVESTIGATION ON A DELTA WING INCORPORATED WITH WINGLETS AT DIFFERENT ANGLES

Bilji C Mathew, P. Dutta, Rushikesh R Savale, Sagar K Sahu
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Abstract

Delta wing has numerous applications across aerospace vehicles. Highly inclined and variable swept back wings have a lot of added advantages in maneuverable fighter airplanes, supersonic cruise airliner; and modern unmanned aerial vehicles that have been equipped with and have deployed low swept back delta wings. Vortex flow across these delta wings is dominant for micro aerial vehicles and mini unmanned aerial vehicles flying at a low speed Reynolds number regime. Many experiments were carried out to study and analyze the aerodynamic flow parameters of delta wings wherein vortex sheet flow patterns were observed and studied at different angles of attack and flow parameters. In this paper we are plotting lift co-efficient and drag coefficient for a flat delta wing with and without winglets at different angles of attack under low Reynolds numbers. Furthermore, simulations are carried out to draw comparisons between the winglets on the basis of span-wise flow velocity vectors.
带不同角度小翼的三角翼气动与实验研究
三角翼在航空航天飞行器上有着广泛的应用。大倾角可变后掠翼在机动战斗机、超音速巡航客机中具有许多附加优势;现代无人驾驶飞行器已经装备并部署了低后掠三角翼。在低速雷诺数状态下飞行的微型飞行器和微型无人驾驶飞行器在三角翼上的涡旋流动占主导地位。为了研究和分析三角翼的气动流动参数,进行了大量的实验,观察和研究了不同迎角和流动参数下的涡片流型。本文绘制了低雷诺数下带小翼和不带小翼的平板三角翼在不同迎角下的升力系数和阻力系数。在此基础上,基于跨流速度矢量进行了仿真比较。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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