Aeroelastic Stability Analyses of Two Counter Rotating Propfan Designs for aCruise Missile Model

摘要

Aeroelastic stability analyses were performed to insure structural integrity oftwo counterrotating propfan blade designs for a NAVY/Air Force/NASA cruise missile model wind tunnel test. This analysis predicted if the propfan designs would be flutter free at the operating conditions of the wind tunnel test. Calculated stability results are presented for the two blade designs with rotational speed and Mach number as the parameters. A aeroelastic analysis code