Paper deals with development for converting Langley 19-ft pressure tunnel for transonic operation; good test section Mach number distributions were obtained up to Mach number 1.26 for length equal to one tunnel height with slot length equal to 2 tunnel heights; performance with short diffusers was never as good as with 6.4° diffuser; rapid test section Mach number changes were achieved by bleeding h-p air into slot flow plenum chamber.


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    Title :

    Development of 8-inch by 8-inch slotted tunnel for Mach numbers up to 1.28


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    72 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :