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Effect of Intercycle Ice Accretions on Airfoil PerformanceThis paper presents the results of an experimental study designed to characterize and evaluate the aerodynamic performance penalties of residual and intercycle ice accretions that result from the cyclic operation of a typical aircraft deicing system. Icing wind tunnel tests were carried out on a 36-inch chord NACA 23012 airfoil section equipped with a pneumatic deicer for several different FAR 25 Appendix C cloud conditions. Results from the icing tests showed that the intercycle ice accretions were much more severe in terms of size and shape than the residual ice accretions. Molds of selected intercycle ice shapes were made and converted to castings that were attached to the leading edge of a 36-inch chord NACA 23012 airfoil model for aerodynamic testing. The aerodynamic testing revealed that the intercycle ice shapes caused a significant performance degradation. Maximum lift coefficients were typically reduced about 60% from 1.8 (clean) to 0.7 (iced) and stall angles were reduced from 17 deg. (clean) to 9 deg. (iced). Changes in the Reynolds number (from 2.0 x 10(exp 6) to 10.5 x 10(exp 6) and Mach number (from 0.10 to 0.28) did not significantly affect the iced-airfoil performance.
Document ID
20030112741
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Broeren, Andy P.
(Illinois Univ. at Urbana-Champaign Urbana, IL, United States)
Bragg, Michael B.
(Illinois Univ. at Urbana-Champaign Urbana, IL, United States)
Addy, Harold E., Jr.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 21, 2013
Publication Date
January 1, 2003
Subject Category
Aerodynamics
Funding Number(s)
CONTRACT_GRANT: DTFA-MB96-6-023
WBS: WBS 22-708-20-02
Distribution Limits
Public
Copyright
Public Use Permitted.
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