GLTRS--Glenn
TITLE AND SUBTITLE:
Navier-Stokes Analysis of the Flowfield Characteristics of an Ice Contaminated Aircraft Wing

AUTHOR(S):
J. Chung, Y. Choo, A. Reehorst, M. Potapczuk, and J. Slater

REPORT DATE:
January 1999

FUNDING NUMBERS:
WU-548-20-23-00

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

PERFORMING ORGANIZATION REPORT NUMBER:
E-11496

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

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-1999-208897
AIAA-99-0375
ICOMP-99-03

SUPPLEMENTARY NOTES:
Prepared for the 37th Aerospace Sciences Meeting & Exhibit sponsored by the American Institute of Aeronautics and Astronautics, Reno, Nevada, January 11-14, 1999. J. Chung, Institute for Computational Mechanics in Propulsion, Lewis Research Center, Cleveland, Ohio; Y. Choo, A. Reehorst, M. Potapczuk, and J. Slater, Lewis Research Center, Cleveland, Ohio. Responsible person, J. Chung, organization code 5840, (216) 433-2411.

ABSTRACT:
An analytical study was performed as part of the NASA Lewis support of a National Transportation Safety Board (NTSB) aircraft accident investigation. The study was focused on the performance degradation associated with ice contamination on the wing of a commercial turboproppowered aircraft. Based upon the results of an earlier numerical study conducted by the authors, a prominent ridgedice formation on the subject aircraft wing was selected for detailed flow analysis using 2dimensional (2D), as well as, 3dimensional (3D) NavierStokes computations. This configuration was selected because it caused the largest lift decrease and drag increase among all the ice shapes investigated in the earlier study. A grid sensitivity test was performed to find out the influence of grid spacing on the lift, drag, and associated angleofattack for the maximum lift (Clmax). This study showed that grid resolution is important and a sensitivity analysis is an essential element of the process in order to assure that the final solution is independent of the grid. The 2D results suggested that a severe stability and control difficulty could have occurred at a slightly higher angleof-attack (AOA) than the one recorded by the Flight Data Recorder (FDR). This stability and control problem was thought to have resulted from a decreased differential lift on the wings with respect to the normal loading for the configuration. The analysis also indicated that this stability and control problem could have occurred whether or not natural ice shedding took place. Numerical results using an assumed 3D ice shape showed an increase of the angle at which this phenomena occurred of about 4 degrees. As it occurred with the 2D case, the trailing edge separation was observed but started only when the AOA was very close to the angle at which the maximum lift occurred.

SUBJECT TERMS:
Aircraft icing; Computational fluid dynamics; Aerodynamic characteristics

NUMBER OF PAGES:
24

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1999/TM-1999-208897.pdf
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