This paper presents the results of a probabilistic flutter study of a mistuned bladed disk using a high fidelity model including both structural and aerodynamic coupling. The approach used in this paper is relatively fast because it does not require any additional information than that required of a tuned flutter analysis, with the exception of the mistuned blade frequencies. The case study shows that the stability of the fleet can be significantly affected by the standard deviation of blade frequencies and the pattern in which they are arranged in the wheel. A method for understanding and identifying the beneficial patterns is presented. Copyright © 2006 by ASME.