Tunnel is of variable density type, designed for pressures from 1/3 to 3 atmospheres at Mach numbers from M-0.3 to M-3.0 on 16-in. long model; reasons behind choice of tunnel. (see also Flight v 67 n 2421 June 17 1955 p 825-6, 849)
Armstrong Whitworth's new supersonic wind-tunnel
Aeroplane
Aeroplane ; 88 , n 2291
1955
5 pages
Article (Journal)
English
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Armstrong Whitworth's new supersonic wind-tunnel
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