NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Results of Low Power Deicer tests on a swept inlet component in the NASA Lewis Icing Research TunnelTests were conducted under a USAF/NASA Low Power Deicer program on two expulsive technologies to examine system performance on hardware representative of a modern aircraft part. The BF Goodrich Electro-Expulsive Deicing System and Pneumatic Impulse Ice Protection system were installed on a swept, compound curve, engine inlet component with varying leading edge radius, and tested through a range of icing and system operating conditions in the NASA Lewis Icing Research Tunnel. A description of the experimental procedure and results, including residual ice thickness, shed ice particle size, and changes in system energy/pressure characteristics are presented.
Document ID
19930038554
Document Type
Conference Paper
Authors
Bond, Thomas H. (NASA Lewis Research Center Cleveland, OH, United States)
Shin, Jaiwon (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
AIAA PAPER 93-0032
Meeting Information
AIAA, Aerospace Sciences Meeting and Exhibit(Reno, NV)
Distribution Limits
Public
Copyright
Other