ICE PROTECTION ANALYSIS OF AIRCRAFT TAIL LEADING EDGE
عنوان مقاله: ICE PROTECTION ANALYSIS OF AIRCRAFT TAIL LEADING EDGE
شناسه ملی مقاله: AEROSPACE10_059
منتشر شده در دهمین همایش انجمن هوافضای ایران در سال 1389
شناسه ملی مقاله: AEROSPACE10_059
منتشر شده در دهمین همایش انجمن هوافضای ایران در سال 1389
مشخصات نویسندگان مقاله:
M. H. Esteki - Aeronautical Design Center of Iran Aircraft Manufacturing Industries Co.
H Khani
خلاصه مقاله:
M. H. Esteki - Aeronautical Design Center of Iran Aircraft Manufacturing Industries Co.
H Khani
The objective of this paper is to analyze the ice formation prediction on the leading edge of aircraft tail with a numerical commercial code for an aircraft with especial mission that modified from the basic version and requires extension of the fuselage. Heat flux requirement with critical icing conditions have been case studied for root and tip horizontal and vertical aircraft tail to achieve 0, 10, 20°C Surface temperature and anti ice full evaporative condition. Then the necessary power of anti ice full evaporation has been comprised by surface temperatures that heat fluxes have been calculated. Finally details of the 2D droplet trajectory calculation and impingement have analyzed. Also, compares the impingement characteristics with those obtained from the 2D code
کلمات کلیدی: Ice formation, Evaporation, Droplet trajectory, Compressible flow
صفحه اختصاصی مقاله و دریافت فایل کامل: https://civilica.com/doc/134339/