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Boeing Research Aerodynamic/Icing Tunnel Capabilities and Calibration
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Abstract
Flight testing of aircraft under natural icing conditions can be extremely tedious, time consuming, costly, and somewhat risky. However, such testing has been required to demonstrate the effectiveness of anti-icing systems and to certify new aircraft models.
To reduce the need for extensive flight testing, Boeing has built a new icing tunnel that has the capability for developing ice shapes and evaluating anti-icing features on full scale sections of critical parts of the aircraft. The icing tunnel was made by modifying an existing 5 ft by 8 ft Boeing Wind Tunnel to add icing capabilities. This paper describes the design specifications, the tunnel capabilities, and the major equipment systems and presents the results of the tunnel calibration relative to the specified requirements.
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Citation
Cain, G., Yurczyk, R., Belter, D., and Chintamani, S., "Boeing Research Aerodynamic/Icing Tunnel Capabilities and Calibration," SAE Technical Paper 940114, 1994, https://doi.org/10.4271/940114.Also In
References
- Chintamani, S. H. Sawyer, R. S. Experimental Design of Expanding Third Corner for the Boeing Research Aerodynamic Icing Tunnel AIAA Paper 92-031 January 1992
- Ide, R. F. “Liquid Water Content and Droplet Size Calibration of the NASA Lewis Icing Research Tunnel,” NASA Technical Memorandum 102447 January 1990