Abstract
Abstract : The report presents the results of an analysis to determine how certain aerodynamic flutter parameters are changed from their free stream values by the existence of supersonic and hypersonic nose shock waves and expansions. The results indicate that nose shock waves and expansions can create a new set of 'free stream' conditions for flutter analyses. These new free stream conditions can be sufficiently different from the undisturbed 'free stream' condition to warrant their detailed analyses in the supersonic and hypersonic vehicle.
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