بررسی عملکرد آیرودینامیکی یک مدل تجربی بال شکل‌پذیر با طول دهنۀ متغیر

نوع مقاله : مقاله پژوهشی

نویسندگان

1 صنعتی مالک اشتر

2 دانشگاه مالک اشتر

3 امیر کبیر

چکیده

در تحقیق حاضر، طرح شکل‌پذیر بال با طول دهنۀ متغیر روی بال یک پهپاد به‌منظور دست‌یابی به عملکرد بهینه در رژیم‌های مختلف پروازی در تونل باد مورد بررسی قرارگرفته است. برای اجرای این طرح، یک بال شکل‌پذیر به‌همراه مکانیزم‌های مربوط به آن طراحی، ساخته و تست ‌شده است. آزمایش‌ها در یک تونل باد سرعت‌‌پایین در سرعت‌های 35، 60 و 80 متر بر ثانیه در محدودۀ عدد ‌رینولدز بین 250×〖10〗^3 تا 620×〖10〗^3 انجام‌گرفته است.‌ برای اجرای طرح شکل‌پذیر، تغییر طول بال نسبت به بال پایه، 38 درصد و میزان تغییر ضریب منظری نیز 74 درصد می‌باشد. نتایج تجربی نشان‌دهندۀ بهبود ویژگی‌های آیرودینامیکی بال شکل‌پذیر نسبت به بال پایه می‌باشد، این مسئله به فرم کاهش پسای القایی و نیروی رانش موردنیاز و افزایش ضریب برآ، راندمان آیرودینامیکی و افزایش مداومت و برد پرواز ظاهرشده است. طبق نتایج، مداومت و برد پروازی بال شکل‌پذیر نسبت به بال پایه به‌ترتیب 17 و 5 درصد افزایش داشته است. مطالعات تجربی انجام‌شده نشان می‌دهد که بیشترین راندمان آیرودینامیکی مدل بال در زاویۀ حمله 4 درجه و حداکثر مقدار آن 8/14 برای بال پایه، 3/16 برای بال شکل‌پذیر با افزایش طول 50 درصد(5 سانتی‌متر) و 4/17 درصد برای بال شکل‌پذیر با افزایش طول 100 درصد
(10 سانتی‌متر) می‌باشد. در این تحقیق هم‌چنین نشان داده ‌شده است که چگونه می‌توان از طرح بال شکل‌پذیر به‌عنوان یک روش جایگزین برای کنترل حرکات غلت به‌جای روش کنترل غلت سنتی (سطوح کنترل شهپر) استفاده نمود. به‌نحوی‌ که در مقایسه با کنترل غلت معمولی استفاده از روش طول متغیر قدرت کنترل غلت را افزایش خواهد داد.

کلیدواژه‌ها

عنوان مقاله [English]

Aerodynamic Performance Investigation of an Experimental Variable-Span Morphing Wing Model

نویسندگان [English]

  • abbas tarabi 1
  • sajjad gasemloo 2
  • mahmoud mani 3
1 دانشگاه مالک اشتر
2 امیر کبیر
3 امیر کبیر
چکیده [English]

In this paper, the implementation of the variable-span Morphing wing(VSMW) on the wings of a UAV to achiev the optimal performance for various flight regimes is studied in wind tunnels. For the implementation of this plan, a morphing wing with its related mechanism is designed, built and tested. Tests were carried out at a low- speed wind tunnel with speeds of 35, 60 and 80 m/s in the range of Reynolds Number between 250×〖10〗^3 to 620×〖10〗^3. For the implementation of the morphing wing plan, the maximum deviation of wing span relative to Basewing (BW) is 38 percent and change of aspect ratio is 74% percent. Experimental results showed the improved aerodynamic properties of VSMW compared to BW. These improvements are in the form of reduction of induced drag, thrust required and increasing of lift coefficient, aerodynamic efficiency, endurance and rang. According to the results, endurance and range for VSMW comparison to BW, respectively 17 and 5 percent increased. The experimental studies show that the maximum aerodynamic efficiency of the wing model occurs at 4 degree angle of attack with the maximum value being 14.8 for the base wing, 16.3 for the morphing wing with 50 percent (5 cm) extension in wing span, and 17.4 % for the morphing wing with 100 percent (10 cm) span extension. This research also shows how VSMW can be used as an alternative method of roll control instead of the regular method (i.e. using aileron control surfaces) as it provides more roll control power than the regular method.

کلیدواژه‌ها [English]

  • Morphing Wing
  • Variable Span
  • wind tunnel
  • Range and Endurance
  • Aerodynamic Coefficient

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