Effects of icing on the aerodynamic performance of high lift airfoilsA 2D compressible Navier-Stokes solver capable of analyzing multi-element airfoils is described. The flow field is divided into multiple zones. In each zone, the governing equations are solved using an implicit finite difference scheme. The flow solver is validated through a study of the aerodynamic characteristics of a GA(W)-1 configuration, for which good quality measured surface pressure data and load data are available. The solver is next applied to a study of the effects of icing on an iced 5-element airfoil configuration, experimentally studied at NASA Lewis Research Center. It is demonstrated that the formation of ice over the leading edge slat and the main airfoil can lead to significant flow separation, and a significant loss in lift, compared to clean configurations.
Document ID
19930036147
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sankar, L. N. (NASA Lewis Research Center Cleveland, OH, United States)
Phaengsook, N. (NASA Lewis Research Center Cleveland, OH, United States)
Bangalore, A. (Georgia Inst. of Technology Atlanta, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-0026
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit