دانش و فناوری هوافضا

دانش و فناوری هوافضا

محاسبه‌ گرمایش آیروترمودینامیکی و تشعشعی دماغه‌های ماوراءصوت فناشونده با استفاده از تلفیقی از نتایج کد CTCA ، عدد بی‌بعد RN و روش مرجع صفحه‌ تخت آنتالپی

نوع مقاله : مقاله پژوهشی

نویسندگان
1 دانشجوی دکتری، مکانیک- تبدیل انرژی ، دانشگاه آزاد اسلامی واحد غرب، تهران
2 دانشیار، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک‌اشتر
3 استادیار، گروه مکانیک، دانشگاه آزاد اسلامی واحد غرب، تهران
چکیده
کدCTCA یکی از ابزارهای مؤثر و صحه‌گذاری شده جهت محاسبه‌ گرمایش آیروترموینامیکی و تشعشعی اعمال شده بر دیواره‌ دماغه‌های ماوراءصوت است. در این تحقیق از عدد بی‌بعدRN جهت تعیین مرز بین گرمایش آیروترمودینامیکی و تشعشعی دماغه‌های بیان شده و از روش آنتالپی مرجع جهت محاسبه‌ گرمایش آیروترمودینامیکی صفحه‌ تخت در زوایای حمله‌ مختلف استفاده شده است. به دلیل بالا بودن زمان حل، کاربران کدCTCA ، استفاده از آن را جهت اهداف طراحی اولیه، منطقی نمی دانند. لذا محققان همواره به دنبال تدوین یک رابطه‌ تحلیلی جهت محاسبه‌ شار حرارتی این دماغه‌ها، با دقت یکسان در مقایسه با روش‌های عددی بوده‌اند. هدف از این تحقیق تدوین معادلات صریح و تحلیلی EECAR_AN جهت محاسبه‌ مستقیم شار حرارتی دماغه‌ سامانه‌های ماوراءصوت در گذر زمان با بهره‌گیر‌ی از تلفیقی از نتایج آزمایشات پروازی، کد CTCA، عدد بی‌بعد RN و روش آنتالپی مرجع صفحه تخت در محیط نرم‌افزار کامسول تحت عنوان الگوریتم CTCA+است. نتایج تحلیل‌ها نشان داد که حداکثر میزان خطا جهت محاسبه‌ شار حرارتی کل نسبت به کد CTCA کمتر از 7 درصد بود.
کلیدواژه‌ها

موضوعات


عنوان مقاله English

Calculating the aerothermodynamics heating and radiation heat flux of ablative noses by using the combined of CTCA results, RN number & reference enthalpy method of flat plate

نویسندگان English

Saadolah Rostami 1
jamasb pirkandi 2
Maherdad Malekzadie deerin 3
1 Department of Mechanic- Energy Conversion Engineering, Azad University, West Tehran, Iran.
2 Associate Professor, Faculty of Aerospace, Malek Ashtar University of Technology, Iran
3 Department of Mechanic Engineering, Azad University, West Tehran, Iran.
چکیده English

The Validated CTCA Code is one of the effective tools for calculating the aerothermodynamics and radiation heating applied to the wall of the hypersonic noses. Also, the dimensionless RN number is to determine the limit of aerothermodynamics and radiation heating of the mentioned noses and the reference enthalpy method is for calculating the aerothermodynamics heating of a flat plate at different angles of attack. Due to the high solution time, the users of this code do not think it is logical to use it for preliminary design purposes. so researchers always have been seek to develop an analytical relationship to calculate the heat flux of these noses, with the same accuracy compared to numerical methods. the purpose of this research is to compile explicit and analytical or EECAR_ AN equations for the direct calculation of the heat flux of the hypersonic vehicles over time, using a combination of the results of CTCA code, RN number and the flat plate reference enthalpy method in the platform of CAMSOL software, it is called CTCA+ Algorithm. The results showed that the maximum amount of error for calculating the total heat flux compared to CTCA code was less than 7%.

کلیدواژه‌ها English

CTCA code, RN number, EECAR_AN Equations, CTCA+ Algorithm, CAMSOL Software, Reference Enthalpy Method, Flight Tests
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