Concept Design of a H.A.U.'s Subsonic Wind Tunnel

H대학교 아음속 풍동 개념설계

  • 장조원 (한국항공대학교 항공운항학과) ;
  • 전창수 (한국항공대학교 항공우주 및 기계공학부) ;
  • 김문상 (한국항공대학교 항공우주 및 기계공학부) ;
  • 이열 (한국항공대학교 항공우주 및 기계공학부) ;
  • 문희장 (한국항공대학교 항공우주 및 기계공학부) ;
  • 송병흠 (한국항공대학교 항공운항학과) ;
  • 김학봉 (한국항공대학교 항공우주 및 기계공학부)
  • Published : 2005.12.31


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.