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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Advanced design features in Canada's supersonic wind tunnel


    Additional title:

    SAE -- Paper


    Conference:

    SAE Meeting ; 1962 Supersonic



    Publication date :

    1962


    Size :

    42 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :


    ADVANCED DESIGN FEATURES IN CANADA'S SUPERSONIC WIND TUNNEL

    SECORD, L. C. / TILLSON, L. J. P. | SAE Technical Papers | 1962


    Canada's first supersonic aircraft

    Engineering Index Backfile | 1957


    Supersonic wind tunnel optimization

    BUSHNELL, D. / TRIPI, R. | AIAA | 1986


    Continuous supersonic wind tunnel

    Engineering Index Backfile | 1955


    Continuous supersonic wind tunnel

    Engineering Index Backfile | 1955