Accession Number : AD0745838

Title :   A Study of Supersonic Cascade Flutter,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF

Personal Author(s) : Chalkley,Henry George

Report Date : JUN 1972

Pagination or Media Count : 157

Abstract : Supersonic flow past oscillating flat plate cascades with supersonic leading-edge locus is analysed using a linearized method of characteristics valid for arbitrary frequencies and an elementary analytical theory valid only for low frequencies of oscillation. These two methods are extensions of previous work by Teipel and Sauer for the single airfoil in an unbounded supersonic flow to the case of airfoils oscillating in cascade. Included is the determination of pressure distributions and both a two-degree-of-freedom (bending and torsion) flutter analysis and a single-degree-of-freedom (torsion) flutter analysis. Numerically determined flutter boundaries are presented for various primary parameters such as, Mach number, solidity, stagger angle, density ratio, structural damping coefficient, and elastic axis position. (Author)

Descriptors :   (*SUPERSONIC AIRFOILS, FLUTTER), (*AXIAL FLOW COMPRESSORS, CASCADE STRUCTURES), LEADING EDGES, OSCILLATION, BENDING, RESONANT FREQUENCY, TORSION, MATHEMATICAL MODELS, COMPUTER PROGRAMS, THESES

Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE