TY - CONF
T1 - Computation of three-dimensional viscous transonic flows with the LU factored scheme
AU - Obayashi, Shigeru
AU - Fujii, Kozo
N1 - Funding Information:
The authors would like to thank Dr. M. Yoshida, National Aerospace Laboratory, for his help with the vectorization of the code. Fujitsu company is acknowledged for giving an opportunity to use new supercomputers VP200 and VP400. The authors would also like to thank Mr. S. Shirayama, Univ. of Tokyo, and Prof. K. Kuwahara, The Institute of Space and Astronautical Science, for their help with displaying the computational results.
Publisher Copyright:
© American Institute of Aeronautics and Astronautics, Inc., 1985. All rights reserved.
PY - 1985
Y1 - 1985
N2 - The LU-ADI factored scheme has been successfully applied to solve the three-dimensional compressible “thin-layer” Navier-Stokes equations. The computations are carried out for the slightly supersonic flow over a hemisphere cylinder at high incidence and the transonic flow over a swept wing. To simulate these complicated flow fields, the fine grid distributions up to about 200, 000 points were used on a new Japanese supercomputer of 1 GFLOPS. The total cpu time for each case was less than two hours. The result for the flow over a hemisphere cylinder at high incidence revealed the detailed structure of the vortical flow field. The result for the flow over a swept wing shows that the three-dimensional shock-induced separation is well captured. These results indicate the capability of the present code for the three-dimensional complicated flow field simulations.
AB - The LU-ADI factored scheme has been successfully applied to solve the three-dimensional compressible “thin-layer” Navier-Stokes equations. The computations are carried out for the slightly supersonic flow over a hemisphere cylinder at high incidence and the transonic flow over a swept wing. To simulate these complicated flow fields, the fine grid distributions up to about 200, 000 points were used on a new Japanese supercomputer of 1 GFLOPS. The total cpu time for each case was less than two hours. The result for the flow over a hemisphere cylinder at high incidence revealed the detailed structure of the vortical flow field. The result for the flow over a swept wing shows that the three-dimensional shock-induced separation is well captured. These results indicate the capability of the present code for the three-dimensional complicated flow field simulations.
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U2 - 10.2514/6.1985-1510
DO - 10.2514/6.1985-1510
M3 - Paper
AN - SCOPUS:85006323929
T2 - 7th Computational Physics Conference, 1985
Y2 - 15 July 1985 through 17 July 1985
ER -