Anti-Icing Simulation in Wet Air of a Piccolo System using FENSAP-ICE

Document Number: 2007-01-3357

Date Published: September 2007

Author(s):
Hongzhi Wang - Newmerical Technologies International
Pascal Tran - Newmerical Technologies International
Wagdi G. Habashi - Newmerical Technologies International
Yingchun Chen - The First Aircraft Institute (AVIC I)
Miao Zhang - The First Aircraft Institute (AVIC I)
Lijuan Feng - The First Aircraft Institute (AVIC I)

Abstract:
In order to ensure flight safety in icing conditions and meet FAA or other national aircraft certification regulations, which require an aircraft to be able to safely operate throughout the icing envelope of Part 25 Appendix C, ice protection mechanisms have to be employed on critical locations of an aircraft. Among different anti-icing mechanisms, hot bleed air systems are the most reliable and efficient ones, and are widely used on commercial aircraft to protect critical surfaces such as leading edge wing panels and high lift devices, empennage surfaces and engine nacelle lip. Due to the complexity of anti-icing experiments and flight tests, advanced numerical simulation of complex thermal anti-icing systems has been highly anticipated as a supplementary design and certification tool. CHT3D, the new 3-D Conjugate Heat transfer module of FENSAP-ICE for the simulation of hot air and electro-thermal ice protection, will be presented in this paper. A complex engineering application with FENSAP-ICE for a main wing anti-icing system design will be also presented including airflow prediction, droplet impingement, and unprotected ice accretion of an entire aircraft, as well as fully coupled anti-icing simulation of a preliminary design piccolo tube system for a slat section.

File Size: 2096K
Product Status: In Stock

Included in: V116-2007

See other papers presented at 2007 SAE Aircraft and Engine Icing International Conference, September 2007, Seville, SPAIN, Session: In-flight Ice Protection System Modeling

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