The major problem in the design of a low-noise supersonic wind tunnel is to reduce the noise radiated from the turbulent, nozzle-wall boundary layer. This broadband noise is generally the dominant disturbance mode in the wind tunnels at Mach numbers greater than about 2.5. These acoustic disturbances are propagated along Mach lines in supersonic flow; hence, their sources are located far upstream of the test section at so-called 'acoustic origins' near the nozzle wall. It is shown that tailoring the nozzle contour to reduce the Mach number and boundary-layer thickness at the acoustic origins significantly reduces the noise levels in the upstream part of the test rhombus. (Jensen)


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    Title :

    New technique for reducing test section noise in supersonic wind tunnels


    Additional title:

    Neue Technik zur Laermminderung an Pruefteilen in Ueberschallwindkanaelen


    Contributors:

    Published in:

    AIAA Journal ; 18 , 1 ; 5-6


    Publication date :

    1980


    Size :

    2 Seiten, 2 Bilder, 11 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    New Technique for Reducing Test Section Noise in Supersonic Wind Tunnels

    J. B. Anden / P. C. Stainback / I. E. Beckwith | AIAA | 1980


    A new technique for reducing test section noise in supersonic wind tunnels

    ANDERS, J. / STAINBACK, P. / BECKWITH, I. | AIAA | 1978



    Supersonic Wind Tunnels

    Keil, C.G. | Emerald Group Publishing | 1960


    Supersonic wind tunnels

    Keil, C.G. | Engineering Index Backfile | 1960