NASA, FAA, ONERA, and other partner organizations have embarked on a significant, collaborative research effort to address the technical challenges associated with icing on large scale, three-dimensional swept wings. These are extremely complex phenomena important to the design, certification and safe operation of small and large transport aircraft. There is increasing demand to balance trade-offs in aircraft efficiency, cost and noise that tend to compete directly with allowable performance degradations over an increasing range of icing conditions. Computational fluid dynamics codes have reached a level of maturity that they are being proposed by manufacturers for use in certification of aircraft for flight in icing. However, sufficient high-quality data to evaluate their performance on iced swept wings are not currently available in the public domain and significant knowledge gaps remain.
NASA,FAA,ONERA Swept-Wing Icing and Aerodynamics: Summary of Research and Current Status
2015 SAE International Conference on Icing of Aircraft, Engines, and Structures ; 2015 ; Prague, Czechoslovakia
22.06.2015
Sonstige
Keine Angabe
Englisch
Computations of Swept Wing Icing Aerodynamics
AIAA | 2019
|NTRS | 1977
|Swept Wing Icing Physics Studies at NASA Glenn Research Center 1990-2006
SAE Technical Papers | 2007
|ONERA Research Icing Wind Tunnel
TIBKAT | 2022
|