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This paper deals with whirl flutter analysis of aircraft structures. It gives the theoretical background of the whirl flutter phenomenon and aircraft certification-related issues. After that, the ordinary and optimization-based analytical approaches are described. The optimization based analytical procedure is used to determine the whirl flutter stability boundaries for the certification speed. The focus is on the application of the optimization-based approach on a full-span model of an aircraft structure. The necessary adjustments of a stick computational model to make it applicable as a full-span and also the modification of the optimization solution are described. The methodology is demonstrated on the model of a twin-engine turboprop commuter aircraft. The evaluated results include the available choices of both propeller rotation directions, i.e. CW-CW and CW-CCW. Finally, the outlook and the future work on the described topic is outlined.

APPLICATION OF WHIRL FLUTTER OPTIMIZATION-BASED SOLUTION TO FULL-SPAN MODEL OF TWIN TURBOPROP AIRCRAFT