Internal weapons carriage in high performance aircraft is often adversely affected by the severe aero-acoustic environment produced with the weapons bay doors open. In order to obtain a better understanding of this fluid dynamics problem, basic static and oscillatory pressure data were obtained for Mach 0.6 to 3.0 flows over shallow rectangular cavities in a generic flat plate model. Cavity length to depth ratios were varied from approximately 5 to 10. Static pressure data characteristic of both open and closed cavity flows were obtained. An improved Rossiter method is presented that satisfactorily predicts the possible frequency modes within the cavity. Highest fluctuating pressures occur on the aft bulkhead, peaking near Mach 1.5 for the conditions tested. Aero-acoustic levels are substantially reduced by installing suppression fences (spoilers) at subsonic and low supersonic conditions. Acoustic levels generally drop rapidly above Mach 1.5. (Peters)


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    Title :

    AERO-acoustic measurements for Mach 0.6 to 3.0 flows past rectangular cavities


    Additional title:

    Luftschallmessungen fuer Stroemungen mit einer Machzahl von 0,6 bis 3,0, hinter rechtwinkligen Hohlrauemen


    Contributors:

    Published in:

    Publication date :

    1980


    Size :

    12 Seiten, 15 Bilder, 2 Tabellen, 14 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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