The paper describes a unique supersonic inlet with a subsonic axial component, torsional flutter cascade experiment, wherein a computer controlled electromagnetic airfoil excitation system is used to simulate the fundamental time-dependent airfoil interaction; assure periodicity; and control the interblade phasing angle. Experimental data are presented which indicate the variation and significance of the cascade inlet Mach number, the stagger angle, and the interblade phasing angle on the cascade dynamic torsional aeroelastic characteristics. (Author)
Research on Aeroelastic Phenomena in Airfoil Cascades: Supersonic Inlet Torsional Flutter
1974
49 pages
Report
Keine Angabe
Englisch
Supersonic Inlet-Torsional Cascade Flutter
AIAA | 1975
|Supersonic chordwise bending flutter in cascades
Tema Archiv | 1975
|Using Aeroelastic Modes for Nonlinear Panel Flutter At Arbitrary Supersonic Yawed Angle
British Library Conference Proceedings | 2002
|