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 Aeroplane v 88 n 2291 June 17 1955 p 821-5)
Armstrong Whitworth's new supersonic wind-tunnel
Flight
Flight ; 67 , n 2421 ; p 825-826 + 849
1955
Aufsatz (Zeitschrift)
Englisch
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Armstrong Whitworth's new supersonic wind-tunnel
Engineering Index Backfile | 1955
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Engineering Index Backfile | 1955
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Engineering Index Backfile | 1955
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