Methods employed in stabilizing stagnation temperature, settling chamber pressure and transonic Mach number in 5×5 ft high speed wind tunnel of Nat Aeronautical Establishment, Ottawa, Canada; under most demanding flow conditions temperature drop of less than 10 F is achieved by 210 tons of thin walled tubing placed in last 90 ft of last of 3 storage vessels connected in series; other details.
Advanced design features in Canada's supersonic wind tunnel
SAE -- Paper
SAE Meeting ; 1962 Supersonic
1962
42 pages
Conference paper
English
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ADVANCED DESIGN FEATURES IN CANADA'S SUPERSONIC WIND TUNNEL
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