COMPUTER PROGRAM FOR CALCULATING UNSTEADY AERODYNAMIC COEFFICIENTS FOR CASCADES IN SUPERSONIC AXIAL FLOW.
Recent interest in supersonic and hypersonic flight has renewed interest 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. This report describes 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's instructions, and test cases.