Open AccessWind Tunnel Testing Study of Segmented Slat with Simulated Icing for Civil Aircraft
Author(s) -
Yang Liu,
Xing Zhou
Publication year - 2021
Publication title -
journal of physics. conference series
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.21
H-Index - 85
eISSN - 1742-6596
pISSN - 1742-6588
DOI - 10.1088/1742-6596/1820/1/012003
Subject(s) - icing , wind tunnel , aerodynamics , lift to drag ratio , lift (data mining) , icing conditions , drag , lift coefficient , aerospace engineering , marine engineering , structural engineering , engineering , environmental science , meteorology , computer science , physics , reynolds number , data mining , turbulence
Icing accretion on civil aircraft have a severe impact on safety and performance, and the leading edge icing of wing resulting in maximum lift coefficient reduction, drag increasing, stalling incidence forward, control and stability worsening and even stalling. This article is to explore aerodynamic characteristics variation of civil aircraft with simulated icing accretion on different segmented slats through the means of wind tunnel testing, and the typical aerodynamic characteristic parameters involve maximum lift coefficient, stalling incidence and lift-to-drag ratio. Forces and moments measurement for configurations of the cruising, take-off and landing had been carried out, the results and analysis of testing data could be used for anti-icing design and operation strategy making.