مطالعه عددی اثر ضریب پیشروی بر روی دینامیک استال پره روتور بالگرد در پرواز رو به‌جلو

نوع مقاله : مقاله مستقل

نویسندگان

1 دانشجوی دکتری، دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران

2 استاد، دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران

10.22044/jsfm.2025.15285.3913

چکیده

در این تحقیق با استفاده از شبیه‌سازی عددی به بررسی پدیده دینامیک استال پره بالگرد با زاویه پیچ متغیر در دو ضریب پیشروی3 .0 = μ و μ =0.35 پرداخته شده است. به منظور شبیه‌سازی میدان جریان تراکم پذیر سه‌بعدی، معادلات متوسط‌گیری‌شده ناویر استوکس با استفاده از روش گسسته‌سازی حجم محدود حل شده است. شبکه مورد استفاده از نوع ترکیبی بوده و از مدل برای مدل‌سازی جریان توربولانسی بهره گرفته شده است. جهت اعتبارسنجی شبیه‌سازی انجام شده، از نتایج تست پروازی بالگرد AH1-G استفاده شده که نتایج این مقایسه نشان‌دهنده دقت مناسب شبیه‌سازی در این تحقیق می‌باشد. نتایج این تحقیق نشان می‌دهد که بر خلاف انتظار، در ناحیه پس‌رونده روتور شدت و تعداد استال‌های ایجاد شده در مقطع مورد مطالعه (r/R=0.778) در ضریب پیشروی 3 .0 بیشتر از شدت و تعداد استال‌ها در ضریب پیشروی 35 .0 می‌باشد. در ناحیه پیش‌رونده روتور، استال ایجاد شده در ضریب پیشروی 35 .0 شدید تر بوده به طوری که ضریب گشتاور پیچشی در ناحیه پس از استال 89% کمتر (منفی‌تر) از مقدار آن در ضریب پیشروی 3 .0 می‌باشد. آشکارسازی الگوی جریان نشان می‌دهد که توسعه دینامیک استال در هر دو ضریب پیشروی با جدایش جریان از نزدیکی لبه فرار شروع و سپس به بالادست گسترش یافته و همزمان به دلیل وجود جریان شعاعی به سمت نوک پره خم شده است.

کلیدواژه‌ها

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