مطالعه عددی اثرات کنترل جریان به وسیله جت مولد گردابه پالسی بر جریان آشفته روی یک ایرفویل

نوع مقاله : مقاله پژوهشی

نویسنده

عضو هیات علمی / پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری

چکیده

در این مقاله کنترل جدایش جریان به وسیله عملگر جت مولد گردابه پالسی روی یک ایرفویل با مقطع NASA SC(2)-0714 در جریان با رینولدز 106×1، به صورت عددی مورد بررسی قرار گرفته است. جریان جت پالسی با فرکانس 40 هرتز و سیکل کاری 50 درصد از یک شکاف خارج می‌شود. شبیه‌سازی در زوایای حمله 14، 16 و 18 درجه در حوالی زاویه واماندگی انجام شده است. برای درک بهتر از چگونگی عملکرد جت مولد گردابه پالسی، اثرات ناشی از جت هوای ناپایا روی مشخصات لحظه‌ای و متوسط‌گیری زمانی جریان استخراج شده و تغییرات فیزیکی و الگوی گردابه‌ای جریان روی سطح ایرفویل مطالعه شده است. نتایج نشان می‌دهد تحریک جریان توسط عملگر جت پالسی در زاویه حمله 14 و 16 درجه، جدایش جریان را با موفقیت به تأخیر انداخته است. در نتیجه راندمان آیرودینامیکی مقطع بال به ترتیب 8/14 و 2/33 درصد افزایش می‌یابد. همچنین در زاویه حمله 18 درجه که در منطقه پسا واماندگی قرار دارد، تحریک کنترلی، جدایش جریان بزرگ روی ایرفویل را حذف کرده و جریان در قسمت قابل توجهی از وتر ایرفویل، به سطح ایرفویل متصل می‌شود.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Numerical investigation of the flow control by a pulsed vortex generator jet on the turbulent flow of an airfoil

نویسنده [English]

  • Soheila Abdolahipour
Aerospace Research Institute
چکیده [English]

In this article, the flow separation control by the vortex generator jet actuator on an airfoil with NASA SC(2)-0714 cross-section in the flow with Reynolds 1×106 has been numerically investigated. The pulsed jet has a frequency of 40 Hz and a duty cycle of 50%. The simulation has been done at the angles of attack of 14, 16 and 18 degrees where the flow separation on the airfoil surface starts and then comes to a stall condition. In this research, in order to better understand how the pulsed vortex generator jet works, the effects of the unsteady jet on the instantaneous and time-averaged flow characteristics are extracted and the vortices pattern of the flow on the airfoil surface has been investigated. The results indicate that the actuation effectively delays the flow separation at the angles of attack of 14 and 16 degrees. As a result, the aerodynamic efficiency of the wing section increases by 14.8% and 33.2%, respectively. At the angle of attack of 18 degrees, which is in the post-stall condition, the actuation eliminates the massive flow separation and the flow attaches to the surface in a significant part of the airfoil chord.

کلیدواژه‌ها [English]

  • Flow control
  • Pulsed vortex generator jet
  • Numerical simulation
  • Unsteady turbulent flow
  • Aerodynamic efficiency
  • Instantaneous and time-averaged characteristics

مراجع

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