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Results of an experimental program investigating the effects of simulated ice on the performance of the NACA 63A415 airfoil with flapAerodynamic data from a test program in the Icing Research Tunnel are reported for a NACA 63A415 airfoil, with fowler flap, clean and with simulated ice shapes. The effect of three ice shapes on airfoil performance are presented, two of the simulated ice shapes are from earlier Icing Tunnel tests. Lift, drag, and moment coefficients are reported for the airfoil, clean and with ice, for angles of attack from approximately zero lift to maximum lift and for flap deflections of 0, 10, 20, and 30 degrees. Surface pressure distribution plots for the airfoil and flap are presented for all runs. Some preliminary oil flow visualization data are also discussed. Large drag penalties were measured in all instances. Maximum lift penalties were in general serious, and depend upon the ice shape and flap deflection.
Document ID
19840008077
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Zaguli, R. J. (Ohio State Univ. Columbus, OH, United States)
Bragg, M. B. (Ohio State Univ. Columbus, OH, United States)
Gregorek, G. M. (Ohio State Univ. Columbus, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:168288
NASA-CR-168288
AARL-TR-83-2
Accession Number
84N16145
Funding Number(s)
PROJECT: RTOP 505-45-02
CONTRACT_GRANT: NAG3-28
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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