Flutter Analysis of a Cascade of Staggered Blades in Subsonic Flow.
TEXAS A AND M UNIV COLLEGE STATION
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The purpose of this report is to utilize a numerical lifting surface theory developed by Rao and Jones to predict the unsteady airloads on an infinite cascade of staggered blades in subsonic compressible flow. An investigation is conducted to determine the effect on the unsteady airloads when parameters such as reduced frequency, interblade stagger angle, interblade spacing, and interblade phase lag are varied over a specific range of values. Once the unsteady airloads have been determined, they are used to perform an aeroelastic analysis of the staggered cascade for a single degree of freedom in torsion and a two degree of freedom system is bending and torsion. Results of the single degree of freedom analysis yields flutter boundaries. A new general flutter program is developed for the two degree of freedom system. The iterative procedure of the flutter program yields the flutter frequency and speed of the cascade reference airfoil as a function of the cascade parameters.
- Fluid Mechanics