مطالعه مشخصات آیرودینامیکی یک ایرفویل فوق بحرانی با پیکره‌بندی برآافزای دو المانی

نوع مقاله : مقاله پژوهشی

نویسندگان

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

2 عضو هیات علمی / دانشگاه صنعتی امیرکبیر

3 عضو هیات علمی / پژوهشگاه هوافضا، وزارت علوم

چکیده

در این تحقیق عملکرد آیرودینامکی مقطع بال NASA SC(2)-0714 با پیکره‌بندی برآافزا شامل المان اصلی بال و فلپ اسلاتی در لبه فرار، به طور تجربی مورد تحقیق قرار گرفته است. آزمایشات در تونل باد و در عدد رینولدز 106×01/1 تحت زوایای حمله مختلف در بازه10- تا 25 درجه و همچنین زاویه انحراف فلپ 0، 20 و 35 درجه انجام شده است. در این آزمایشات با استفاده از اندازه‌گیری‌های نیرویی، راندمان آیرودینامیکی و محدوده واماندگی بال در شرایط مختلف تعیین شده است. همچنین با استفاده از اندازه‌گیری توزیع فشار در مقطع میانه بال اصلی و فلپ و همچنین افت فشار کل در دنباله، به ترتیب موقعیت‌های شروع جدایش جریان و شکل پروفیل دنباله مشخص شده است. نتایج این تحقیق نشان می‌دهد که با طراحی پیکره‌بندی برآافزا و بکارگیری فلپ اسلاتی در لبه فرار بال، ضریب برآی بیشینه در زاویه انحراف فلپ 35 درجه به میزان 58% نسبت به حالت پایه ایرفویل افزایش داشته است.

کلیدواژه‌ها


عنوان مقاله [English]

Experimental Investigation of Aerodynamic Characteristics of a Supercritical Two-Element High-Lift Airfoil

نویسندگان [English]

  • Soheila Abdolahipour 1
  • Mahmoud Mani 2
  • Arash Shams Taleghani 3
1 Faculty member/ Aerospace Research Institute
2 Faculty member/ Amirkabir University of Technology
چکیده [English]

In this research, the aerodynamic performance of a wing with NASA SC (2) -0714 airfoil and a high-lift configuration, including the main element and the slotted flap at the trailing edge, has been experimentally investigated. Experiments were performed in a wind tunnel at a Reynolds number of 1.01×106 under different angles of attack in the range of -10 to 25° and also flap deflection angles of 0, 20, and 35°. In these experiments, aerodynamic efficiency and wing stall characteristics in different conditions have been determined using force measurements. Also, by measuring the pressure distribution in the middle section of the main element and flap, as well as the total pressure loss in the wake, the onset of the flow separation and the wake profile have been determined, respectively. The results of this study show that by designing the high-lift configuration and using the slotted flap at the trailing edge, the maximum lift coefficient at the flap deflection angle of 35° has increased by 58% compared to the airfoil without high-lift configuration.

کلیدواژه‌ها [English]

  • supercritical airfoil
  • high-lift
  • trailing edge flap
  • pressure coefficient
  • total pressure loss
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