دانش و فناوری هوافضا

دانش و فناوری هوافضا

بررسی آیرودینامیکی پهپاد بال لامبدا با لبه حمله سینوسی در محدوده واماندگی

نوع مقاله : مقاله پژوهشی

نویسندگان
1 کارشناس ارشد، گروه مکانیک، دانشکده مهندسی، دانشگاه فردوسی مشهد، مشهد، ایران
2 استاد تمام، گروه مکانیک، دانشکده مهندسی، دانشگاه فردوسی مشهد، مشهد، ایران
3 کارشناسی ارشد، گروه هوافضا، دانشکده مهندسی هوافضا، دانشگاه تهران، تهران، ایران
چکیده
در این پژوهش، تأثیر به‌کارگیری لبه حمله موج‌دار سینوسی بر رفتار آیرودینامیکی یک پهپاد بال‌پرنده بدون دم با بال لامبدا شکل مورد بررسی قرار گرفته است. هندسه اولیه از یک پیکربندی با زاویه عقب‌گرد بال ۵۶ درجه و پیچش ۳- درجه تشکیل شده و سپس با حفظ مساحت بال، تغییر شکل لبه حمله به صورت موج‌های سینوسی اعمال شده است. برای تحلیل دقیق رفتار جریان، شبیه‌سازی‌های عددی ناپایا مبتنی بر مدل آشفتگی از مدل دو معادله‌ای k-ω-sst و معادلات RANS در محیط فلوئنت انجام شده است. محدوده زوایای حمله بین °۲۵ تا °۴۰ انتخاب شده و شرایط جریان در دو هندسه (ساده و موج‌دار) با هم مقایسه گردیده است. برای بررسی دقیق‌تر پدیده واماندگی، تحلیل کانتورهای سرعت و فشار و خطوط جریان در سه مقطع عرضی در طول دهانه بال انجام شده است. نتایج نشان می‌دهد که استفاده از لبه حمله سینوسی، با تشکیل گردابه‌های پایدار در نزدیکی برآمدگی‌ها، موجب تأخیر در جدایش جریان و کاهش شدت واماندگی در مقایسه با هندسه مرجع شده است. علاوه بر آن، ضرایب آیرودینامیکی نشان دادند که بال سینوسی در زوایای بالا، افت برآی ملایم‌تری دارد و گشتاور پیچشی در آن پایداری بیشتری نشان می‌دهد. این بهبودها می‌تواند در ارتقاء پایداری طولی، حفظ کنترل‌پذیری و عملکرد ایمن‌تر پهپادهای بال‌پرنده در زوایای حمله بالا مؤثر واقع شود.
کلیدواژه‌ها

موضوعات


عنوان مقاله English

Aerodynamic investigation of a lambda-wing UAV with a sinusoidal leading edge in the stall range

نویسندگان English

Amir Hosseinikargar 1
Mohammad Hassan Djavareshkian 2
Amirhossein Gholami 3
1 MSc, Mechanical Engineering Department, Ferdowsi University of Mashhad, Mashhad
2 Professor, Mechanical Engineering Department, Ferdowsi University of Mashhad, Mashhad
3 Master Student, Aerospace Engineering Department, University of Tehran, Tehran
چکیده English

This study investigates the aerodynamic effects of introducing a sinusoidal leading edge on a tailless flying wing UAV configuration. The baseline geometry consists of a wing with a sweep angle of 56° and a twist of -3°, which was modified by applying a sinusoidal wave pattern to the leading edge while maintaining the overall wing planform area. Unsteady numerical simulations were conducted in ANSYS Fluent using the SST k−ω turbulence model and Reynolds-Averaged Navier–Stokes (RANS) equations. Simulations were executed for angles of attack ranging from 25° to 40°, and the aerodynamic behavior of the modified and baseline configurations was compared. To better understand stall-related phenomena, flow field data—including velocity and pressure contours as well as streamline distributions—were extracted from three spanwise sections across the wing. The results demonstrate that the wavy leading edge induces organized vortex structures near the crests, which help delay flow separation and reduce the severity of stall compared to the straight-edge design. Furthermore, aerodynamic coefficients indicate that the sinusoidal leading-edge wing exhibits a slower post-stall lift drop and more stable pitching moment behavior. These enhancements improve stability, controllability, and flight safety under high-angle-of-attack conditions for tailless UAVs.

کلیدواژه‌ها English

Flying wing
Sinusoidal leading edge
Numerical simulation
Stall
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