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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    Title :

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


    Contributors:
    J. K. Ramsey (author) / R. E. Kielb (author)

    Publication date :

    1987


    Size :

    54 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English