A study of supersonic cascade flutter
Chalkley, Henry George
MetadataShow full item record
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 distribution and both a two-degree-of -freedom (bending and torsi'on) flutter analysis and a single-degreeof- 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. Also, results are presented for the related problem of supersonic wind tunnel interference (including the effect of tunnel porosity) and airfoil-airfoil interference.
Showing items related by title, author, creator and subject.
Carr, L.W.; Chandrasekhara, M.S. ;Results of recent experimental studies into the effect of compressibility on dynamic stall of oscillating airfoils are reviewed. Stroboscopic schlieren images of the strongly unsteady flow field are presented, showing ...
Chandrasekhara, M.S.; Wilder, M.C.; Carr, L.W. (1993);Experimental results and analysis of the effects of boundary layer tripping on dynamic stall of a transiently pitching airfoil are presented. At low Mach numbers, the tripped airfoil exhibits qualitative similarity with ...
Carr, L.W.; Chandrasekhara, M.S.; Wilder, M.C; Noonan, K.W. ;A multielement airfoil designed for helicopter application has been tested for compressible dynamic stall behavior and has been proven to be a robust dynamic stall-free concept. This slotted airfoil has operated into ...