GLTRS--Glenn
TITLE AND SUBTITLE:
Ice Accretions and Icing Effects for Modern Airfoils

AUTHOR(S):
Harold E. Addy, Jr.

REPORT DATE:
April 2000

FUNDING NUMBERS:
WU-548-21-23-00

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
John H. Glenn Research Center at Lewis Field
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-12228

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Technical Paper

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TP-2000-210031
DOT/FAA/AR-99/89

SUPPLEMENTARY NOTES:
Responsible person, Harold E. Addy, Jr., organization code 5840, (216) 977-7467.

ABSTRACT:
Icing tests were conducted to document ice shapes formed on three different two-dimensional airfoils and to study the effects of the accreted ice on aerodynamic performance. The models tested were representative of airfoil designs in current use for each of the commercial transport, business jet, and general aviation categories of aircraft. The models were subjected to a range of icing conditions in an icing wind tunnel. The conditions were selected primarily from the Federal Aviation Administration's Federal Aviation Regulations 25 Appendix C atmospheric icing conditions. A few large droplet icing conditions were included. To verify the aerodynamic performance measurements, molds were made of selected ice shapes formed in the icing tunnel. Castings of the ice were made from the molds and placed on a model in a dry, lowturbulence wind tunnel where precision aerodynamic performance measurements were made. Documentation of all the ice shapes and the aerodynamic performance measurements made during the icing tunnel tests is included in this report. Results from the dry, lowturbulence wind tunnel tests are also presented.

SUBJECT TERMS:
Aircraft icing; Aerodynamic characteristics

NUMBER OF PAGES:
291

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2000/TP-2000-210031.pdf
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