Numerical investigation of simultaneous blowing and suction on the wing's airfoil of a maneuverable aircraft
Article Type:
Research/Original Article (دارای رتبه معتبر)

In this article, a numerical investigation of the effect of simultaneous suction and blowing on an airfoil is studied to reduce the separation bubble. This investigation was done at Re=8.5×106 and the simulations are done by commercial Fluent software. First, the suction and blowing systems are used at different blowing and suction angles (30, 45 and 90 degrees) along with their location (distance ratio 0, 0.1, 0.2, 0.3, 0.6, 0.7 and 0.8) were investigated. In this study, the ratio of lift to drag, pressure coefficient, velocity and pressure contours were compared in different cases compared to the one with no slot, and finally the best state was determined. The results of this study showed that the suction on the leading edge and blowing on the tailing edge can improve the aerodynamic performance of the airfoil at an angle of attack of 17 degree. The best performance was the blowing at a distance ratio of 0.6C and suction at 0.1C, which increased the lift-to-drag ratio by 55%. Compared to the one without any slot.

Journal of Mechanical Engineering, Volume:52 Issue: 4, 2023
203 to 211  
دانلود و مطالعه متن این مقاله با یکی از روشهای زیر امکان پذیر است:
اشتراک شخصی
با عضویت و پرداخت آنلاین حق اشتراک یک‌ساله به مبلغ 990,000ريال می‌توانید 60 عنوان مطلب دانلود کنید!
اشتراک سازمانی
به کتابخانه دانشگاه یا محل کار خود پیشنهاد کنید تا اشتراک سازمانی این پایگاه را برای دسترسی نامحدود همه کاربران به متن مطالب تهیه نمایند!
  • حق عضویت دریافتی صرف حمایت از نشریات عضو و نگهداری، تکمیل و توسعه مگیران می‌شود.
  • پرداخت حق اشتراک و دانلود مقالات اجازه بازنشر آن در سایر رسانه‌های چاپی و دیجیتال را به کاربر نمی‌دهد.
In order to view content subscription is required

Personal subscription
Subscribe for 50 € euros via PayPal and download 60 articles during a year.
Organization subscription
Please contact us to subscribe your university or library for unlimited access!