بررسی عددی تاثیر حفره دایره‌ای بر روی کنترل جریان جدا‌شده پره نوسانی ناکا 0012 تحت شرایط واماندگی دینامیکی

نوع مقاله : مقاله پژوهشی

نویسندگان

1 استادیار ، دانشگاه امام علی (ع)،تهران، ایران

2 استادیار، پژوهشگاه هوا فضا،تهران، ایران

چکیده

در این پژوهش، اثر حفره بر روی مشخصه‌های پیچشی پره ناکا 0012 تحت شرایط واماندگی دینامیکی به صورت عددی مورد مطالعه و بررسی قرار گرفت و جریان آشفته تراکم‌ناپذیر ناپایا نیز در دوبعد شبیه‌سازی گردید. دو نمونه حفره دایره‌ای با شعاع c05/0R= در دو موقعیت مشخص c13/0x= یا c6/0x= نسبت به لبه حمله پره تعیین شد تا اثر موقعیت حفره بر روی پارامتر‌های آیرودینامیکی پره همچون ضرایب برآ، پسا، گشتاور پیچشی و بازده آیرودینامیکی (نسبت ضریب برآ به پسا) با فرض عدد رینولدز 106 و فرکانس کاهش-یافته 15/0 تحلیل گردد. نتایج نشان داد که حفره در موقعیت دوتر نسبت به لبه حمله رفتار بهتری را در بهبود ضریب برآ و بازده آیرودینامیکی پره نوسانی داشته و مقدار متوسط ضریب برآ برای حالاتی که حفره در دو موقعیت c13/0x= یا c6/0x= قرار گرفته به ترتیب به میزان 57/3% و 18/0% نسبت به حالت ساده افزایش پیدا کرد. مقدار متوسط ضریب پسا نیز به ‌طور نسبی برای حفره در موقعیت c6/0x= به میزان 25/3% کاهش و برای حفره در موقعیت c13/0x= به میزان 97/3% نسبت به حالت ساده افزایش یافت.

کلیدواژه‌ها


عنوان مقاله [English]

Numerical investigation of the cavity effects on the passive flow control of NACA0012 airfoil under dynamic stall conditions

نویسندگان [English]

  • amirhamzeh farajollahi 1
  • mohammad reza salimi 2
  • Mahdi Zakyani Roudsari 2
1 Department of Engineering, Imam Ali University, Tehran, Iran
2 Assistant Professor, Aerospace Research Institute, Tehran, Iran
چکیده [English]

In this study, the effects of a cavity on the pitching characteristics of NACA0012 airfoil under dynamic stall conditions were examined numerically and the transient incompressible turbulent flow was simulated in two dimensions. Two different sets of circular cavities with R=0.05c were set at two different positions of x=0.13c and x=0.6c from the leading edge (LE) to investigate the effect of cavity position on the aerodynamic parameters of the airfoil such as lift, drag, and pitching moment coefficients as well as aerodynamic efficiency (lift to drag ratio), using Re=106 and reduced frequency of kf=0.15. Results indicated that the cavity at distant location from the airfoil LE showed a better performance in improving the lift coefficient along with aerodynamic efficiency of the pitching airfoil and the averaged values of the lift coefficient for cavities at x=0.13c and x=0.6c locations increased by 3.57% and 0.18%, respectively compared to the baseline. The averaged value of the drag coefficient for the cavity located at x=0.6c decreased by 3.25% and for the cavity at x=0.13c went up by 3.97% in comparison to the clean airfoil.

کلیدواژه‌ها [English]

  • cavity
  • flow control
  • NACA0012 airfoil
  • pitching motion
  • dynamic stall
  • numerical modeling

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