دانش و فناوری هوافضا

دانش و فناوری هوافضا

طراحی تحلیلی، بهینه‌سازی چندهدفه و شبیه‌سازی عددی ورودی مافوق صوت دو رمپه

نوع مقاله : مقاله پژوهشی

نویسندگان
1 دکتری هوافضا، دانشکده مهندسی مکانیک، دانشگاه علم و صنعت، تهران، ایران
2 دانشجوی دکتری مکانیک، دانشکده مهندسی مکانیک، دانشگاه علم و صنعت، تهران، ایران
3 استاد، دانشکده مهندسی مکانیک، دانشگاه علم و صنعت، تهران، ایران
چکیده
در این پژوهش، یک چارچوب ترکیبی تحلیلی-عددی برای طراحی و بهینه‌سازی چندهدفه ورودی‌های مافوق صوت دو رمپه تحت شرایط برخورد شوک بر لبه (SOL) در عدد ماخ 2.5 توسعه داده شده است. در مرحله اول، یک روش تحلیلی بر پایه روابط شوک مایل و معیار اوسواتیچ برای تولید یک هندسه بهینه مرجع صورت پذیرفت. سپس با استفاده از روابط شوک مایل و معیارهای هندسی SOL، یک پایگاه داده جامع از هندسه‌های معتبر ایجاد گردید. پس از آن، فرآیند بهینه‌سازی چندهدفه با در نظر گرفتن دو هدف متضاد کمینه‌سازی طول کل رمپ‌ها و بیشینه‌سازی بازیابی فشار سکون انجام شد. نتایج نشان می‌دهد که در محدوده طرح‌های معتبر SOL، حتی با تغییر 28‌% در طول کل رمپ‌ها، مقدار بازیابی فشار سکون بسیار پایدار است (تغییری حدود 0.1‌%). این یافته بیانگر آن است که انتخاب طرح با کمترین طول، تقریباً هیچ ضرر آیرودینامیکی قابل‌توجهی ندارد، در حالی‌که مزایای ساختاری چشمگیری از جمله کاهش وزن و پیچیدگی سیستم را به همراه می‌آورد. اعتبارسنجی عددی با شبیه‌سازی‌های دوبعدی غیرلزج تأیید می‌کند که رویکرد پیشنهادی ابزاری کارآمد برای طراحی سریع ورودی‌های مافوق صوت است.
کلیدواژه‌ها
موضوعات

عنوان مقاله English

Analytical design, multi-objective optimization, and numerical simulation of a two-ramp supersonic inlet

نویسندگان English

Mostafa Zahedzadeh 1
Hadi Nemati Moghadam 2
Seyed Mostafa Hosseinalipour 3
1 PhD, Department of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran.
2 PhD Student, Department of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran.
3 Professor, Department of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran
چکیده English

In this study, a hybrid analytical-numerical framework is developed for the design and multi-objective optimization of two-ramp supersonic inlets under the shock-on-lip (SOL) condition at Mach 2.5. First, an analytical method based on oblique shock relations and the Oswatitsch criterion is employed to generate a reference optimal geometry. Subsequently, a comprehensive database of valid SOL-compliant geometries is constructed using oblique shock theory and geometric SOL constraints. A multi-objective optimization process is then conducted, considering two conflicting objectives: minimizing total ramp length and maximizing total pressure recovery. Results demonstrate that within the space of valid SOL configurations, total pressure recovery remains highly stable (variation of approximately 0.1%) despite a 28% change in total ramp length. This finding indicates that selecting the shortest-length configuration incurs virtually no significant aerodynamic penalty while offering substantial structural advantages, such as reduced weight and system complexity. Numerical validation via two-dimensional inviscid simulations confirms that the proposed approach is an efficient tool for rapid and design of supersonic inlets.

کلیدواژه‌ها English

Supersonic inlet
Shock-on-lip
Multi-objective optimization
Pareto front
Oswatitsch criterion
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