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MULTI-POINT DESIGN OF A SUPERSONIC WING USING MODIFIED PAR-SEC AIRFOIL REPRESENTATION

Yotsuya, T.; Kanazaki, M.; Makino, Y.; Matsushima, K.;

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This paper discusses the multi-point aerodynamic design of a supersonic wing. Herein, supersonic transport (SST) which cruises over land at a low Mach number (around M = 1.15) and cruises over sea at a high Mach number (around M = 2.0). No sonic boom is said to be heard on the ground because of the “Mach cutoff effect.” This concept requires that high aerodynamic performance should be achieved at a high and a low Mach number cruise, simultaneously. Thus, this study considers a multi-point design aerodynamic problem. The objective functions considered here are employed to maximize the lift–to-drag ratio at cruise speed M=1.15, and M=2.0, simultaneously. Thus, the several flow conditions should be con-sidered. To solve such multi-objective design problem, efficient global optimization (EGO) was applied. The EGO process is based on Kriging surrogate models, which were constructed using several sample designs. Subsequently, the solution space could be explored through the maximization of expected improvement (EI) values that corresponded to the objective function of each Kriging model because the surrogate models provide an estimate of the uncertainty at the predicted point. Once a number of solutions have been obtained for the EI maximization problem by means of a multi-objective genetic algorithm (MOGA), the sample designs could be used to improve the models’ accuracy and identify the optimum solutions at the same time. In this paper, 193 sample points are evaluated for the constructions of the Kriging model, and several design are compared. Remarkably, the kink airfoil should be similar to typical sub-sonic airfoil to achieve higher aerodynamic performance not only at high speed cruise but also low speed cruise in spite of supersonic cruise.

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Palavras-chave: Modified PARSEC Representation, Efficient Global Optimization, Mach Cutoff Effect.,

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DOI: 10.5151/meceng-wccm2012-16733

Referências bibliográficas
  • [1] http://aerioncorp.com/
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  • [3] Matsuzawa, T., K. Matsushima, and Nakahashi, K., “Application of PARSEC Geometry Representation to High-Fidelity Aircraft Design by CFD,” CD proceedings of 5th WCCM/ ECCOMAS2008, Venice, CAS1.8-4 (MS106), 2008.
  • [4] Makino, Y., Low sonic-boom design of a Silent Super Sonic Technology Demonstrator ~ Development of CAPAS and its Application ~, JAXA Special Publication, Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (2007), pp. 697-70
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  • [6] Sobieczky, H., “Parametric Airfoils and Wings,” Notes on Numerical Fluid Mechanics, pp. 71-88, Vieweg 1998.
Como citar:

Yotsuya, T.; Kanazaki, M.; Makino, Y.; Matsushima, K.; "MULTI-POINT DESIGN OF A SUPERSONIC WING USING MODIFIED PAR-SEC AIRFOIL REPRESENTATION", p. 303-313 . In: In Proceedings of the 10th World Congress on Computational Mechanics [= Blucher Mechanical Engineering Proceedings, v. 1, n. 1]. São Paulo: Blucher, 2014.
ISSN 2358-0828, DOI 10.5151/meceng-wccm2012-16733

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