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1405 Design Exploration of Airfoil for Mars Airplane
[in Japanese]
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Yotsuya Tomoyoshi
,
Kanazaki Masahiro
… 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. … Flowfield is solved by the structured Navier-Stokes solver with Baldwin-Lomax turbulent model. …
設計工学・システム部門講演会講演論文集 2010(20), "1405-1"-"1405-6", 2010-10-27
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