著者

金崎 雅博 四谷 智義 奈良 拓矢 松島 紀佐

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.59, no.684, pp.24-26, 2011 (Released:2011-03-03)

参考文献数

4

被引用文献数

1

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The original PARSEC (PARametric SECtion) method can satisfactorily solve the optimization problems involving transonic airfoils by using a few design variables. However, it is difficult to apply this method to the design of airfoils under other conditions such as supersonic flow and low Reynolds number flow. To solve various airfoil design problems by using a few design variables and the PARSEC representation, a modified PARSEC representation is proposed. The capability of the proposed modified representation to solve unknown real-world design problems is investigated; the proposed representation is used along with multi-objective genetic algorithms to solve two types of problems. One is the design of a conventional transonic airfoil that is to be used in the Earth's atmosphere; the other is the design of an airfoil that is to be used in the Martian atmosphere. To evaluate the aerodynamic performance of the airfoils, the structured Navier-Stokes solver is used. The results indicate that better solutions can be obtained by using the proposed PARSEC modification than by using the original PARSEC representation, especially in the Martian atmosphere.

著者

金崎 雅博 奈良 拓矢 四谷 智義

出版者

日本計算工学会

雑誌

計算工学講演会論文集 (ISSN:1342145X)

巻号頁・発行日

no.15, 2010-05

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In this paper, airfoil geometry representation is proposed for the efficient design optimization and the knowledge discovery. Here, PARSEC airfoil representation is improved with several modifications. To investigate the possibility to solve the unknown real-world design problem, two type airfoil geometries is considered using genetic algorithms. One is a conventional transonic airfoil in the Earth atmosphere, the other is a airfoil which can be used in Martian atmosphere To evaluate the aerodynamic performance, the structured Navier-Stokes solver with Baldwin-Lomax turbulent model is used. According to this result, the proposed airfoil representation method can generate the airfoil geometry which achieves high aerodynamic performance as same as NURBS representation. These results suggest that the proposed method can useful for the design exploration methods which include data mining, because the airfoil geometry can be defined with the design variables which show aerodynamic performance directly.

著者

四谷 智義 金崎 雅博

出版者

一般社団法人 日本機械学会

雑誌

設計工学・システム部門講演会講演論文集 2010.20 (ISSN:24243078)

巻号頁・発行日

pp._1405-1_-_1405-6_, 2010-10-27 (Released:2017-06-19)

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In this research, modified PARSEC airfoil representations are developed and they are investigated by the design exploration of airfoils for the Mars airplane. The existent PARSEC airfoil representation method is useful for the aerodynamic optimization and the knowledge discovery, because the original PARSEC airfoil is parameterized based on the aerodynamic theory. In this method, designer can directly define airfoil's parameters, the leading edge radius, the maximum thickness, the maximum camber, and so on, However, the original PARSEC representation cannot use for not subsonic flow (supersonic flow, low Reynolds number flow), because it was parameterized in consideration of a subsonic wing. To solve the several airfoil design problem, modified representation method is constructed and its design performance is investigated by solving multi-objective design problem. This study employs Genetic Algorithm (GA) for exploration of the multi-objective problem. Flowfield is solved by the structured Navier-Stokes solver with Baldwin-Lomax turbulent model. According to these results, the modified airfoil representation method can solve the design problem under the Martian atmosphere better than the original method.