Transition Measurements on the Natural Laminar Flow Wing at Mach 2
作者： Hiroki Sugiura , Kenji Yoshida , Naoko Tokugawa , Shohei Takagi , Akira Nishizawa
DOI: 10.2514/2.3027
关键词:
摘要: Transition characteristics of a supersonic natural laminar flow wing with sweep angle more than 60 deg were measured using hot-film sensors and an infrared camera at Mach 2. The pressure falls very rapidly in the vicinity leading edge wing, such that crossflow instabilities are reduced. slightly accelerates downstream streamwise stabilized. Tests conducted two wind tunnels to estimate transition location flight: quiet tunnel low Reynolds number moderately variable number. As result, effect was confirmed. unit had no on wing. 8 x 10 5 design attack 2, but there is room for further investigation
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