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Navier-Stokes Aerodynamic Simulation of the V-22 Osprey on the Intel Paragon MPPThe paper will describe the Development of a general three-dimensional multiple grid zone Navier-Stokes flowfield simulation program (ENS3D-MPP) designed for efficient execution on the Intel Paragon Massively Parallel Processor (MPP) supercomputer, and the subsequent application of this method to the prediction of the viscous flowfield about the V-22 Osprey tiltrotor vehicle. The flowfield simulation code solves the thin Layer or full Navier-Stoke's equation - for viscous flow modeling, or the Euler equations for inviscid flow modeling on a structured multi-zone mesh. In the present paper only viscous simulations will be shown. The governing difference equations are solved using a time marching implicit approximate factorization method with either TVD upwind or central differencing used for the convective terms and central differencing used for the viscous diffusion terms. Steady state or Lime accurate solutions can be calculated. The present paper will focus on steady state applications, although time accurate solution analysis is the ultimate goal of this effort. Laminar viscosity is calculated using Sutherland's law and the Baldwin-Lomax two layer algebraic turbulence model is used to compute the eddy viscosity. The Simulation method uses an arbitrary block, curvilinear grid topology. An automatic grid adaption scheme is incorporated which concentrates grid points in high density gradient regions. A variety of user-specified boundary conditions are available. This paper will present the application of the scalable and superscalable versions to the steady state viscous flow analysis of the V-22 Osprey using a multiple zone global mesh. The mesh consists of a series of sheared cartesian grid blocks with polar grids embedded within to better simulate the wing tip mounted nacelle. MPP solutions will be shown in comparison to equivalent Cray C-90 results and also in comparison to experimental data. Discussions on meshing considerations, wall clock execution time, load balancing, and scalability will be provided.
Document ID
20020012216
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Vadyak, Joseph
(NASA Ames Research Center Moffett Field, CA United States)
Shrewsbury, George E.
(NASA Ames Research Center Moffett Field, CA United States)
Narramore, Jim C.
(NASA Ames Research Center Moffett Field, CA United States)
Montry, Gary
(NASA Ames Research Center Moffett Field, CA United States)
Holst, Terry
(NASA Ames Research Center Moffett Field, CA United States)
Kwak, Dochan
Date Acquired
August 20, 2013
Publication Date
January 1, 1995
Subject Category
Aerodynamics
Meeting Information
Meeting: Computational Aeroscience Workshop
Location: Moffett Field, CA
Country: United States
Start Date: March 7, 1995
End Date: March 9, 1995
Funding Number(s)
PROJECT: RTOP 505-99-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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