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.
Computer Program for Calculating Unsteady Aerodynamic Coefficients for Cascades in Supersonic Axial Flow
1987
54 pages
Report
No indication
English