Abstract

This paper presents a parallel mesh deformation solver using radial basis function (RBF) interpolation. The solver computes the displacement of each internal point independently without using the topological relations, and is further accelerated by an incremental approach based on the data reduction algorithm. The incremental approach makes full use of the matrix and solution of the previous step during the greedy selection procedure, and gives a better initial solution of the current RBF system of equations. To enhance the robustness and efficiency of the solver in parallel, for nonpredefined boundary movement, each CPU process computes the same interpolation function; for predefined movement, an additional process can be used to calculate the interpolation function one step earlier and broadcast it to other processes. Four typical mesh motion cases are simulated to demonstrate the deforming capability and parallel performance of the proposed method. Finally, several parametric setting rules of the deformation approach are presented for better usage.

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Acknowledgments

This paper was supported by the National Natural Science Foundation of China under Grants Nos. 11502296, 61772542, and 61561146395; the Foundation of National University of Defense Technology under Grant No. ZDYYJCYJ20140101; the Open Research Program of China State Key Laboratory of Aerodynamics under Grant No. SKLA20160104; and the Defense Industrial Technology Development Program under Grant No. C1520110002.

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Go to Journal of Aerospace Engineering
Journal of Aerospace Engineering
Volume 31Issue 3May 2018

History

Received: Oct 6, 2017
Accepted: Feb 2, 2018
Published online: Mar 8, 2018
Published in print: May 1, 2018
Discussion open until: Aug 8, 2018

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Ph.D. Candidate, College of Computer, National Univ. of Defense Technology, No. 109 Deya Rd., Changsha 410073, P.R. China. E-mail: [email protected]
Associate Professor, College of Computer, National Univ. of Defense Technology, No. 109 Deya Rd., Changsha 410073, P.R. China (corresponding author). E-mail: [email protected]
Ph.D. Candidate, College of Aerospace Science and Engineering, National Univ. of Defense Technology, No. 109 Deya Rd., Changsha 410073, P.R. China. E-mail: [email protected]
Ph.D. Candidate, College of Computer, National Univ. of Defense Technology, No. 109 Deya Rd., Changsha 410073, P.R. China. E-mail: [email protected]
Assistant Professor, College of Aerospace Science and Engineering, National Univ. of Defense Technology, No. 109 Deya Rd., Changsha 410073, P.R. China. E-mail: [email protected]
Zhenghua Wang [email protected]
Professor, College of Computer, National Univ. of Defense Technology, No. 109 Deya Rd., Changsha 410073, P.R. China; Professor, State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, P.O. Box 211, Mianyang 621000, P.R. China. E-mail: [email protected]
Xiaogang Deng [email protected]
Professor, College of Aerospace Science and Engineering, National Univ. of Defense Technology, No. 109 Deya Rd., Changsha 410073, P.R. China; Professor, College of Computer, National Univ. of Defense Technology, No. 109 Deya Rd., Changsha 410073, P.R. China. E-mail: [email protected]

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