The objective of phase two of a current investigation sponsored by NASA Langley Research Center is to demonstrate the measurement of aerodynamic forces/moments, including the effects of exhaust gases, in magnetic suspension and balance system (MSBS) wind tunnels. Two propulsion simulator models are being developed: a small-scale and a large-scale unit, both employing compressed, liquified carbon dioxide as propellant. The small-scale unit was designed, fabricated, and statically-tested at Physical Sciences Inc. (PSI). The large-scale simulator is currently in the preliminary design stage. The small-scale simulator design/development is presented, and the data from its static firing on a thrust stand are discussed. The analysis of this data provides important information for the design of the large-scale unit. A description of the preliminary design of the device is also presented.


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    Title :

    Propulsion Simulator for Magnetically-Suspended Wind Tunnel Models


    Contributors:
    P. B. Joshi (author) / C. L. Goldey (author) / G. P. Sacco (author) / P. L. Lawing (author)

    Publication date :

    1991


    Size :

    32 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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