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Application of a Third Order Upwind Scheme to Viscous Flow over Clean and Iced WingsA 3-D compressible Navier-Stokes solver has been developed and applied to 3-D viscous flow over clean and iced wings. This method uses a third order accurate finite volume scheme with flux difference splitting to model the inviscid fluxes, and second order accurate symmetric differences to model the viscous terms. The effects of turbulence are modeled using a Kappa-epsilon model. In the vicinity of the sold walls the kappa and epsilon values are modeled using Gorski's algebraic model. Sampling results are presented for surface pressure distributions, for untapered swept clean and iced wings made of NACA 0012 airfoil sections. The leading edge of these sections is modified using a simulated ice shape. Comparisons with experimental data are given.
Document ID
19970006701
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bangalore, A. (Georgia Inst. of Tech. Atlanta, GA United States)
Phaengsook, N. (Georgia Inst. of Tech. Atlanta, GA United States)
Sankar, L. N. (Georgia Inst. of Tech. Atlanta, GA United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1994
Publication Information
Publisher: American Inst. of Aeronautics and Astronautics
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-202616
AIAA Paper 94-0485
NAS 1.26:202616
Meeting Information
Meeting: Aerospace Sciences
Location: Reno, NV
Country: United States
Start Date: January 10, 1994
End Date: January 13, 1994
Sponsors: American Inst. of Aeronautics and Astronautics
Accession Number
97N13595
Funding Number(s)
CONTRACT_GRANT: NAG3-768
Distribution Limits
Public
Copyright
Public Use Permitted.

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