COMPUTER PROGRAM FOR CALCULATING UNSTEADY AERODYNAMIC COEFFICIENTS FOR CASCADES IN SUPERSONIC AXIAL FLOW.

Published

Report

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.

Duke Authors

Cited Authors

  • Ramsey, JK; Kielb, RE

Published Date

  • December 1, 1987

Published In

Book Title

  • NASA Technical Memorandum

International Standard Serial Number (ISSN)

  • 0499-9320

Citation Source

  • Scopus