CFD zonal modeling of leading-edge ice effects for a complete aircraftA simplified, uncoupled zonal procedure was utilized to assess the capability of numerically simulating icing effects on a Boeing 727-200 aircraft. The computational approach combines potential flow, plus boundary layer simulations by VSAERO for the un-iced aircraft forces and moments, with Navier-Stokes simulations by ARC3D for the incremental forces and moments due to iced components. These are compared with wind tunnel longitudinal force and moment data. Although the computational results compared favorably with the test data in the linear angle of attack range, it is clear that for general aircraft icing calculations, a multiblock Navier-Stokes code will be required for the viscous component of this zonal method.
Document ID
19930038604
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Summa, J. M. (NASA Lewis Research Center Cleveland, OH, United States)
Strash, D. J. (NASA Lewis Research Center Cleveland, OH, United States)
Lednicer, D. A. (Analytical Methods, Inc. Redmond, WA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-0167
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit