بررسی عددی اثر هندسه اسلات بر روی عملکرد دهانه ورودی هوای فراصوت

نوع مقاله : مقاله پژوهشی

نویسندگان

1 عضو هیات علمی / مجتمع دانشگاهی مکانیک، دانشگاه صنعتی مالک اشتر

2 دانشجوی کارشناسی ارشد / مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر

3 عضو هیات علمی / مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر

چکیده

به منظور بهبود عملکرد دهانه ورودی هواگردهای فراصوت، روش‌های مختلفی جهت کنترل و تضعیف اثرات مضر متقابل موج ضربه‌ای و لایه مرزی مورد استفاده قرار می‌گیرد در این تحقیق کنترل غیرفعال اسلات به‌عنوان یک روش نوین و کاربردی بدین منظور ارائه شده و اثر آن بر عملکرد دهانه ورودی فراصوتی بررسی شده است. بدین منظور ابتدا یک دهانه ورودی هوای فراصوت مستطیلی با عدد ماخ طراحی 2/۲ مدل‌سازی و شبکه‌بندی شده و با استفاده از روش دینامیک سیالات محاسباتی به منظور دستیابی به یک شبکه ایده‌آل، موضوع استقلال از شبکه در حالت سه بعدی مورد بررسی قرارگرفته و مناسب‌ترین شبکه جهت ادامه کار انتخاب شده است. به منظور حصول اطمینان از درستی روش حل، نتایج به‌دست آمده از شبیه‌سازی عددی با نتایج سایر محققان مقایسه‌ و اعتبارسنجی شده است. در این تحقیق ابتدا عملکرد ورودی در عدد ماخ طراحی 2/2 بدون اسلات مورد بحث و بررسی قرار گرفته سپس با ایجاد اسلات‌ و بررسی پارامترهای مختلف آن، عملکرد آن‌ها مقایسه شده است. نتایج نشان می‌دهدکه استفاده از اسلات سبب افزایش فشار بازیافتی و درنتیجه بالا رفتن عملکرد دهانه ورودی هوا در شرایط خارج از طرح نیز می‌شود و ایجاد اسلات سبب تاخیر در رسیدن موج قائم به دهانه ورودی و کنترل جریان بطور موثر می‌شود.
در ادامه با انتخاب بهترین حالت اسلات، عملکرد ورودی در شرایط خارج از طرح در اعداد ماخ 2 و 4/2 در دو حالت با و بدون اسلات ارائه و مقایسه شده‌اند و بهترین هندسه از بین آن‌ها انتخاب شده است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Numerical Analysis of Effect of Slot Geometry on Supersonic Air Inlet Performance

نویسندگان [English]

  • mehrdad bazazzadeh 1
  • Hojjat Tolouei 2
  • Mahdi Hashemabadi 3
1 Faculty of Mechanical Engineering, Malek Ashtar University of Technology, Iran
2 Malek-Ashtar University shainshar
3 Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Iran.
چکیده [English]

Various methods are used to control and attenuate the adverse effects of shock wave/boundary layer interactions (SWBLIs) and improve the performance of supersonic aircraft inlet. In this study, passive slot control is presented as a new, practical method for this purpose and its effect on supersonic inlet performance is investigated. To do so, a rectangular supersonic air inlet is first modeled and meshed at design Mach number of 2.2 and mesh independency is examined using three-dimensional (3D) computational fluid dynamics (CFD) method to achieve an ideal mesh; the most suitable mesh is selected to continue the work. The results of numerical simulations are compared with those of other studies and validated to ensure the correctness of the solution. In this paper, the inlet performance is first discussed without slots at design Mach number of 2.2 and, then, its performance is evaluated by creating slots and considering various parameters. The results indicated that using slots increased the pressure recovery and, consequently, enhanced the inlet performance in off-design conditions. It was also found that creating slots caused the vertical waves to reach the inlet with a delay and effectively controlled the flow. Then, after selecting the best slot, the inlet performance was presented and compared in off-design conditions at Mach numbers of 2 and 2.4, both with and without slots; finally, the best geometry was determined

کلیدواژه‌ها [English]

  • Supersonic air inlet
  • Inlet performance
  • Slot
  • Mach number
  • Pressure recovery

مراجع

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