A Study of Panel Flutter Including a Turbulent Boundary Layer.
Final rept. 1 Jul 73-30 Jun 74,
AERONAUTICAL RESEARCH ASSOCIATES OF PRINCETON INC N J
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A theory is developed for calculating flutter boundaries of a finite or infinite length array of panels in a supersonic flow including the effects of a turbulent boundary layer. The panel flutter analysis is based on the exact Laplace transform method of Zeydel and Yates. The aerodynamic theory is based on an integral perturbation method. Calculations are given for finite and infinite length panels. Very small boundary layer thickness are discussed for stabilizing the traveling wave type of flutter in a finite length panel.
- Fluid Mechanics