This low speed wind tunnel at CARDC is a large scale, double experimental section wind tunnel solely designed and built in China. It is primarily used for experiments in the aerodynamic characteristics of airplanes and other aircraft; in ground wind load of guided missiles and space vehicles; in large attack angle of airplanes and guided missiles; in large prototypes; in aerodynamics of helicopters and vertical short takeoff aircraft; and in industrial aerodynamics (e.g., architecture, bridges, fans and automobiles. It passed national certification at the end of 1983 and was officially released for use. This wind tunnel is an open-circuit, closed double experimental section in series, large scale low speed wind tunnel. Its entire length is 237 m with a maximum width of 40 m and a maximum height of 20.5 m. It consists of air intake assembly, stabilization section, first convergence section, first experimental section, second experimental section, first divergence section, fan section, second divergence section, and air exhaust assembly.
8 m x 6 m Low Speed Wind Tunnel at the Chinese Aerodynamic Research and Development Center
1986
18 pages
Report
No indication
English
Test Facilities & Equipment , Aerodynamics , Aircraft , Wind tunnels , Aerodynamic characteristics , Air , Air intakes , Angle of attack , Assembly , Bridges , Convergence , Exhaust gases , Fans , Ground level , Guided missiles , Helicopters , Industries , Low velocity , Passenger vehicles , Prototypes , Short takeoff aircraft , Spacecraft , Stabilization , Vertical takeoff aircraft , Wind , Foreign technology , Translations
Wind tunnel for aerodynamic research
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