Noise measurements pertaining mainly to the static firing, launch, 0 and exit flight phases are presented for three rocket-powered vehicles 4 in the Project Mercury test program. Both internal and external data 4 from onboard recordings are presented for a range of Mach numbers and dynamic pressures and for different external vehicle shapes. The main sources of noise are noted to be the rocket engines during static firing and launch and the aerodynamic boundary layer during the high-dynamic-pressure portions of the flight. Rocket-engine noise measurements along the surface of the Mercury Big Joe vehicle were noted to correlate well with data from small models and available data for other large rockets. Measurements have indicated that the aerodynamic noise pressures increase approximately as the dynamic pressure increases and may vary according to the external shape of the vehicle, the highest noise levels being associated with conditions of flow separation. There is also a trend for the aerodynamic noise spectra to peak at higher frequencies as the flight Mach number increases.


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    Title :

    Noise Considerations for Manned Reentry Vehicles


    Contributors:
    D. A. Hilton (author) / W. H. Mayes (author) / H. H. Hubbard (author)

    Publication date :

    1960


    Size :

    18 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Noise Considerations for Manned Reentry Vehicles

    Hilton, David A. / Mayes, William H. / Hubbard, Harvey H. | NTRS | 1960


    Noise considerations for manned reentry vehicles

    Hilton, David A. / Mayes, William H. / Hubbard, Harvey H. | TIBKAT | 1960


    Noise considerations for manned reentry vehicles

    Hilton, D. A. / Mayes, W. H. / Hubbard, H. H. | NTRS | 1960