سال انتشار: ۱۳۸۹

محل انتشار: دهمین همایش انجمن هوافضای ایران

تعداد صفحات: ۵

نویسنده(ها):

M. H. Esteki – Aeronautical Design Center of Iran Aircraft Manufacturing Industries Co.
H Khani –

چکیده:

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