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장조원,전창수,김문상,이열,문희장,송병흠,김학봉,Chang, J.W.,Jeon, C.S.,Kim, M.S.,Lee, Y.,Moon, H.J.,Song, B.H.,Kim, H.B. 한국항공운항학회 2005 한국항공운항학회지 Vol.13 No.4
A closed-circuit type wind tunnel is designed, which has a test section with the dimensions $1.2(W){\times}1.2(H){\times}3.4(L)$. A subsonic wind tunnel is designed to improves educational circumstances and promote ground tests. It is constituted of an exchangeable test section, first and second diffusers, a fan, a settling chamber, a contraction, and 4 corners. The maximum velocity in the test section is 70m/s and the contraction ratio is 6.25:1. Input power in the wind tunnel is about 96.1 kw (128.8 hp) and its energy ratio is 3.89. It has the dimension of about $7.4(W){\times}3.6(H){\times}21.7m(L)$. The wind tunnel designed in this investigation will be an effective educational and investigational equipment.