نوع مقاله : علمی پژوهشی

نویسندگان

1 دانشجوی کارشناسی ارشد، گروه مکانیک، دانشکده مهندسی، دانشگاه فردوسی مشهد، مشهد، ایران

2 استاد، گروه مکانیک، دانشکده مهندسی، دانشگاه فردوسی مشهد، مشهد، ایران

10.22034/jtae.2024.8.2.2

چکیده

پژوهش حاضر، به بررسی تأثیر فنس بر گردابه های راس بال و سطوح کنترلی در هواپیما با استفاده از روش عددی می پردازد. در طراحی و قرار دادن فنس های بال، ابعاد متوسط استخراج شده از گردابه های راس بال در زوایای حمله مختلف به کار گرفته شده است. همچنین، فنس ها با ابعاد مشخص شده در سه ارتفاع و سه موقعیت مختلف در طول بال نصب شده (طول فنس برابر با میانگین طول گردابه در آن قسمت و ارتفاع فنس 30 درصد قطر گردابه آن قسمت است) و در زوایای حمله 7 تا 16 درجه بررسی شده‌اند. گام بعدی، طراحی ابعاد فنس به روش بهینه سازی تک هدفه است. هدف دستیابی به بهترین طراحی که با حداقل زمان و هزینه به یک راه حل بهینه همگرا شود. طراحی فنس ها در سه نقطه بر اساس ابعاد گردابه با روش عددی انجام می شود. با این حال، تجزیه و تحلیل عددی (CFD) به زمان محاسباتی زیادی نیاز دارد، برای حل این، از تابع پایه شبکه عصبی (RBF) و مدل کریجینگ (Kriging) با قرار دادن شرایط اولیه مسئله و نتایج حل عددی در صورت وجود فنس، استفاده شده تا با تعیین مناسب ترین مکان، ضریب گشتاور غلتشی را به حداقل رسانیم.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Design and optimization of the wing fence of a lambda-shaped aircraft model to reduce the rolling moment coefficient

نویسندگان [English]

  • Mohammad hossein Moghimi Esfandabadi 1
  • Mohammad Hassan Djavareshkian 2

1 MSc Student, Professor, Department of Mechanics, Faculty of Engineering, Ferdowsi University of Mashhad, Mashhad, Iran

2 Professor, Department of Mechanics, Faculty of Engineering, Ferdowsi University of Mashhad, Mashhad, Iran

چکیده [English]

This research investigates the effect of fence on wingtip vortices and control surfaces in a bird-like aircraft using numerical methods. In designing and placing the fence, average dimensions extracted from wing root vortices at different angles of attack have been used. In addition, the fence with specified dimensions have been installed at three heights and three different positions along the wing (the length of the winglet is equal to the average length of the vortex in that part, and the height of the winglet is 30% of the diameter of the vortex in that part) and have been examined at angles of attack ranging from 7 to 16 degrees. The next stage of the study is the optimal design of the dimensions of the control surfaces using a single objective optimization method. The aim of this research is to achieve the best possible design that converges to an optimal solution with minimum time and cost. The design of control surfaces is carried out at three points based on the dimensions of the wing root vortex using numerical methods. However, Computational Fluid Dynamics (CFD) analysis requires a lot of computational time.

کلیدواژه‌ها [English]

  • Wing Fence
  • Optimization
  • Numerical Simulation
  • Lambda Wing
  • UAV
  • Aerodynamic Coefficients
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