بررسی عددی اثر جریان جت-جفت بر واماندگی دینامیکی یک ایرفویل ضخیم

نوع مقاله : مقاله پژوهشی

نویسندگان

1 گروه مهندسی مکانیک، دانشکده مهندسی، دانشگاه حکیم سبزواری، سبزوار، ایران

2 گروه مهندسی مکانیک،‌دانشکده مهندسی، دانشگاه حکیم سبزواری، سبزوار، ایران

3 گروه مهندسی مکانیک، دانشکده مهندسی، دانشگاه صنعتی قوجان، قوچان، ایران

چکیده

واماندگی دینامیکی پدیده‌ای است که به‌واسطه ریزش گردابه­ها بر روی سطح مقطع بال نوسان کننده در زوایای حمله زیاد پدیدار می‌گردد. وقوع واماندگی دینامیکی باعث افت شدید در نیروی برآ و افزایش چشمگیر در نیروی پسا می‌شود. یکی از روش‌های کنترل جریان فعال برای مقابله با این پدیده، جریان جت-جفت می‌باشد. در این مقاله اثر کنترل جریان جت-جفت بر روی ایرفویل نوسانی ناکا 0025 در اعداد رینولدز مختلف بررسی شده است. برای حل عددی جریان سیال، معادلات ناویر-استوکس میانگین رینولدز، به‌صورت دوبعدی، تراکم ناپذیر، ناپایا و با مدل آشفتگی اس اس تی- کی امگا به کمک یک برنامه کامپیوتری خانگی حل گردیده است. برنامه کامپیوتری نوشته‌شده برای این مسئله با نتایج آزمایشگاهی موجود اعتبارسنجی و مطابقت خوبی مشاهده شده است.‌ به‌منظور بررسی اثرات کنترل جریان جت-جفت، سه ضریب ممنتوم مختلف 05/0، 07/0 و 08/0 روی ایرفویل مذکور و پنج عدد رینولدز 104×5، 104×5/7،  105، 105×5/1 و 105×3 بررسی گردیده است. مشاهده می‌گردد که در موارد بررسی شده، ایرفویل پایه در اعداد رینولدز کمتر از 105 رفتار متفاوتی نسبت به اعداد رینولدز بالاتر دارد؛ به‌طوری‌که به‌منظور حذف واماندگی آن نیاز به ممنتوم بیشتر جت یعنی مقدار 08/0 است درصورتی‌که در اعداد رینولدز بالاتر بررسی شده با اعمال ممنتوم 07/0 واماندگی به‌طور کامل حذف گردیده است.

کلیدواژه‌ها

عنوان مقاله [English]

Numerical Investigation of Co-flow Jet Effects on Dynamic Stall of a Thick Airfoil

نویسندگان [English]

  • Abodlamir Khoshnevis 1
  • Shima Yazdani 2
  • Seyed Erfan Salimipour 3
1 Mechanical Engineering Department, Faculty of Engineering , Hakim Sabzevari University, Sabzevar, Iran
2 Mechanical Engineering Department, Faculty of Engineering, Hakim Sabzevari University, Sabzevar, Iran
3 Mechanical Engineering Department, Faculty of Engineering, Quchan University of Technology, Quchan, Iran
چکیده [English]

Dynamic stall is a phenomenon which appears due to the vortex shedding on the oscillating wing section at high angles of attack. Occurrence of the dynamic stall causes a severe decrease in the lift force and huge increase in the drag force. The Co-Flow Jet (CFJ) is one of the active flow controls to prevent this phenomenon. In this paper, the effect of this active flow control on the NACA 0025 airfoil for different Reynolds numbers is investigated. For numerical solution of the fluid flow, the Reynolds-averaged Navier-Stokes equations in two-dimensional, incompressible, and unsteady form with the SST-k-ω turbulence model is solved using an in-house computer code. The developed code is validated with the previous experiment data, and a fairly good agreement is observed. In order to investigate the effects of the CFJ, three different momentum coefficients of 0.05, 0.07 and 0.08 and five Reynolds numbers of 5×104, 7.5×104, 105, 1.5×105, and 3×105 are studied. It is found in the examined cases that the baseline airfoil in the Reynolds numbers of 105 and lower has different behavior compared to the higher Reynolds numbers; while in order to eliminate the dynamic stall, it requires more jet momentum of 0.08, while for the higher investigated Reynolds numbers, by applying the jet momentum of 0.07, the dynamic stall is completely eliminated.

کلیدواژه‌ها [English]

  • Dynamic stall
  • Co-flow jet
  • Numerical investigation
  • Reynolds number
  • Momentum coefficient

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سابقه مقاله

  • تاریخ دریافت: 02 خرداد 1398
  • تاریخ بازنگری: 24 مرداد 1399
  • تاریخ پذیرش: 04 بهمن 1399
  • تاریخ انتشار: 01 تیر 1399

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