Research on Aeroelastic Phenomena in Airfoil Cascades: Supersonic Inlet Torsional Flutter.
GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
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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
- Fluid Mechanics