Recent interest in supersonic and hypersonic flight has renewed interst in developing propulsion systems which include a supersonic axial flow compressor. An important design consideration for the blades in such a compressor is aeroelastic stability. Described is a computer program which calculates the lift and moment coefficients for an oscillating cascade with a supersonic leading edge locus. A brief discussion of the theory (Lane's method) is presented, along with program logic, user instructions, and test cases.


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    Titel :

    Computer Program for Calculating Unsteady Aerodynamic Coefficients for Cascades in Supersonic Axial Flow


    Beteiligte:
    J. K. Ramsey (Autor:in) / R. E. Kielb (Autor:in)

    Erscheinungsdatum :

    1987


    Format / Umfang :

    54 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch