بررسی عددی تأثیر گرمایش آیرودینامیکی بر روی توزیع دمای داخل کابین پرنده مافوق صوت

نوع مقاله : مقاله پژوهشی

نویسندگان

1 عضو هیات علمی / دانشکده مهندسی مکانیک، دانشگاه تربیت دبیر شهید رجایی

2 دانشجوی کارشناسی ارشد / دانشکده مهندسی مکانیک، دانشگاه تربیت دبیر شهید رجایی

چکیده

در این مقاله تأثیر گرمایش آیرودینامیکی به توزیع دمای داخل کابین  پرنده مافوق صوت در حالت­های مختلف عایق­بندی، وجود نیروی گرانش و ارتفاع پروازی به روش دینامیک سیالات محاسباتی با رویکرد حجم محدود پرداخته شده است. برای حل همزمان معادلات در جامد و سیال، از شرط مرزی کوپلینگ در دیواره­ی پوسته استفاده شده است. هوا به صورت گاز ایده­آل فرض شده و رابطه بوزینسک برای تغییرات چگالی آن با دما بکار­گرفته شده است. تغییرات توزیع دمای درون کابین با لحاظ انتقال حرارت جابجایی آزاد به صورت گذرا تا لحظه پروازی 70 ثانیه شبیه­سازی شده است. نتایج به صورت توزیع دما در مقاطع میانی مدل و نمودارهای دما-زمان و دما-مکان در مقاطع میانی و زمان­های گوناگون ارائه شده است.  بررسی نتایج نشان می­دهد که استفاده از عایق موجب کاهش دمای یک نقطه مشخص از کابین به میزان 175 درجه در لحظه پرواز 20 ثانیه می­شود. در این تحقیق از دو روش تجربی و عددی برای صحه­گذاری روی توزیع دما در درون مدل و خارج مدل استفاده شده که دقت خوبی را در نتایج نشان می­دهد.

کلیدواژه‌ها


عنوان مقاله [English]

Numerical analysis of aerodynamic heating effects on temperature distribution inside the ultrasonic bird cabin

نویسندگان [English]

  • Miralam Mahdi 1
  • Majid Rahimi 2
1 Assistant Professor, Mechanical Engineering Department, Shahid Rajaee Theacher Training University
2 Graduated Student, Mechanical Engineering Department, , Shahid Rajaee Theacher Training University
چکیده [English]

In this paper, the effect of aerodynamic heating on temperature distribution inside supersonic bird cabin in different insulation conditions, the existence of gravity force and different flight height has been investigate using a computational fluid dynamics method with the finite volume approach. The coupling boundary condition in the shell wall use to simultaneously to solve the equations in solid and fluid. The air assumed as an ideal gas and the Boussinesq approximation used to changes density with temperature. In-cabin temperature distribution changes in terms of the free Convection heat transfer is simulated transiently up to a flying time of 70 seconds. The results are presented as temperature contour in the middle section of the model, temperature-time and temperature-location diagrams for different times. In this research, experimental and numerical methods are validated the temperature distribution inside and outside the model, which shows good accuracy.

کلیدواژه‌ها [English]

  • aerodynamic heating
  • free convection
  • Supersonic
  • Computational fluid dynamics
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