TY - CONF
T1 - An efficient multiblock method for aerodynamic analysis and design on distributed memory systems
AU - Reuther, J.
AU - Alonso, J. J.
AU - Vassberg, J. C.
AU - Jameson, A.
AU - Martinelli, L.
N1 - Funding Information:
AFOSR under Grant Number AFOSR-F49620-95-1-0259, and USRA through RIACS at the NASA Ames Research Center. The support provided by the IBM-CRA grant is gratefully acknowledged by the authors. The Douglas Aircraft Company is also acknowledged in part for supporting the implemen- tation of the design method on a distributed net- works of workstations. Special thanks are extended to Mark Rimlinger for the generation of the initial meshes used in the calculations presented here.
Funding Information:
Our research has benefited greatly from the support of ARPA under Grant Number N00014-92-J-1796,
Publisher Copyright:
© 1997 by the Authors. Published by the AIAA, Inc.
PY - 1997
Y1 - 1997
N2 - The work presented in this paper describes the application of a multiblock gridding strategy to the solution of aerodynamic design optimization problems involving complex configurations. The design process is parallelized using the MPI (Message Passing Interface) Standard such that it can be efficiently run on a variety of distributed memory systems ranging from traditional parallel computers to networks of workstations. Substantial improvements to the parallel performance of the baseline method are presented, with particular attention to their impact on the scalability of the program as a function of the mesh size. Drag minimization calculations at a fixed coefficient of lift are presented for a business jet configuration that includes the wing, body, pylon, aft-mounted nacelle, and vertical and horizontal tails. An aerodynamic design optimization is performed with both the Euler and Reynolds Averaged Navier-Stokes (RANS) equations governing the flow solution and the results are compared. These sample calculations establish the feasibility of efficient aerodynamic optimization of complete aircraft configurations using the RANS equations as the flow model. There still exists, however, the need for detailed studies of the importance of a true viscous adjoint method which holds the promise of tackling the minimization of not only the wave and induced components of drag, but also the viscous drag.
AB - The work presented in this paper describes the application of a multiblock gridding strategy to the solution of aerodynamic design optimization problems involving complex configurations. The design process is parallelized using the MPI (Message Passing Interface) Standard such that it can be efficiently run on a variety of distributed memory systems ranging from traditional parallel computers to networks of workstations. Substantial improvements to the parallel performance of the baseline method are presented, with particular attention to their impact on the scalability of the program as a function of the mesh size. Drag minimization calculations at a fixed coefficient of lift are presented for a business jet configuration that includes the wing, body, pylon, aft-mounted nacelle, and vertical and horizontal tails. An aerodynamic design optimization is performed with both the Euler and Reynolds Averaged Navier-Stokes (RANS) equations governing the flow solution and the results are compared. These sample calculations establish the feasibility of efficient aerodynamic optimization of complete aircraft configurations using the RANS equations as the flow model. There still exists, however, the need for detailed studies of the importance of a true viscous adjoint method which holds the promise of tackling the minimization of not only the wave and induced components of drag, but also the viscous drag.
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M3 - Paper
AN - SCOPUS:84983119380
SP - 419
EP - 445
T2 - 13th Computational Fluid Dynamics Conference, 1997
Y2 - 29 June 1997 through 2 July 1997
ER -