آیروالاستیک حول یک ایرفویل زبر در جریان گذرصوتی آشفته ناپایا

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشجوی دکتری، دانشگاه فردوسی مشهد،مشهد، ایران

2 استاد، دانشگاه فردوسی مشهد،مشهد، ایران

چکیده

در این پژوهش، اثر زبری و سختی بر آیروالاستیک یک ایرفویل نوسانی در جریان آشفته گذرصوتی ناپایا مورد بررسی شده است. در این تحقیق، برای حل معادلات ناویراستوکس، از روش حجم محدود برای گسسته سازی برمبنای الگوریتم فشار مبنا، اسکیم مرتبه بالا برای محاسبه ترم جابجای و مدل توربولانسی کی-اپسلون استفاده شده است. برای این منظور ، رفتار سیال و سازه در هر گام زمانی جداگانه حل می‌شود و تأثیر هر یک بر روی دیگری در نظر گرفته می‌شود. در این شبیه سازی دوبعدی برای محاسبه ترم‌های جابجایی از اسکیم مرتبه بالایی بر مبنای متغیرهای بی بعد شده و برای شبیه سازی ایرفویل نوسانی، از تکنیک بردار سرعت ورودی نوسانی استفاده شده است. معادلات حرکت دوبعدی، از ترکیب معادلات لاگرانژی سازه با معادلات آیرودینامیکی بدست می‌آیند. نتایج اعتبارسنجی تطابق خوبی را نشان می‌دهد. نتایج شبیه سازی نشان می دهد که قدرت موج ضربه ای در ایرفویل با سطح زبر ضعیف تر شده، موج ضربه ای به سمت لبه فرا حرکت کرده و نوسانات ایرفویل کاهش می یابد. همچنین با افزایش سختی سازه‌ای، میرایی نوسانات افزایش و پسا کاهش می یابد.

کلیدواژه‌ها

عنوان مقاله [English]

Aerolastic Around Rough Airfoil During Turbulent Unsteady Transonic Flow

نویسندگان [English]

  • M.R. Saber 1
  • Mohammad Hassan Djavareshkian 2
1 PhD student Ferdowsi University of Mashhad, Mashhad, Iran
2 Professor, Ferdowsi University of Mashhad, Mashhad, Iran
چکیده [English]

In this paper, the effect of roughness and stiffness on the aeroelasticity of an oscillating airfoil during turbulent unsteady transonic flow has been studied. In this simulation, the finite volume method is used to discretize the equations to solve the Navier-Stokes equations. In this pressure-based algorithm, a high-resolution scheme for convection term and 𝜿-ε turbulence model are used. For computing convection terms, a Normalized Variable Diagram technique is used. Here the technique of inlet velocity vector oscillation is applied. In addition, a modified 𝜿-ε model for compressible flow is applied to simulate Navier Stokes equations. The two-dimensional motion equations are obtained from the Lagrangian equations, which are combined with the aerodynamic equations. The results of validation show that the extracted data has a desirable accuracy. Furthermore, the FSI results show that, for rough airfoils, the strength of the shock wave is weakened, the shock wave moves to the trailing edge, and the oscillation of the airfoil is reduced. Also, with increasing structural stiffness, the damping of oscillations increases, and drag decreases.

کلیدواژه‌ها [English]

  • "FSI"
  • " Aeroelastic"
  • " Oscillation
  • "Transonic"
  • "Roughness"
  • " Stiffness"
  • " Unsteady"

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مراجع

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سابقه مقاله

  • تاریخ دریافت: 09 خرداد 1400
  • تاریخ بازنگری: 30 آبان 1400
  • تاریخ پذیرش: 20 دی 1400
  • تاریخ انتشار: 01 اسفند 1400

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