M AXIMUM lift characteristics and vibratory loading of the rotor are limiting factors in rotorcraft performance [1]. To expand the range of helicopter capabilities, active control methods to improve performance and reduce vibratory loading are being developed. For example, Grohmann et al. [2] produced oscillatory trailing-edge deflections and active trailing-edge tabs by applying layers of piezoelectric fibers on the skin of an airfoil section and activating the piezoelectric fibers at frequencies ranging from ω∕Ω 2 to 6. In hover, aerodynamic pressures reduced the control authority by approximately 20%, indicating that aeroelastic effects must be included to produce an accurate aeroelastic analysis of the blade section. Gandhi et al. [3] designed and optimized a variable-camber blade section by integrating piezoelectric stacks into the blade structure and applying a compliant skin on the blade surface. Highly compliant materials are applied in the construction of active airfoils to reduce the work required to deform the airfoil. Flexibility in camber can adversely affect the stability characteristics of a rotor blade. To determine the effects of camber flexibility on aeroelastic stability, Murua et al. [4] conducted a two-dimensional numerical aeroelastic experiment using the aerodynamic model of Peters et al. for flexible airfoils [5] and included pitch, plunge, and parabolic camber modes. Numerical results indicated that camber effects alone can cause flutter and that the camber mode significantly influences stability boundaries when coupled with pitch and plunge modes. In forward flight and during maneuvers, the increased presence of transonic flow, dynamic stall, and wake effects add to the complexity of the physics. Thus, the solution of the Navier– Stokes equations is required to obtain accurate performance characteristics. The ability of a surface-conforming aeroelastic methodology formed from coupling an unsteady Reynolds-averaged Navier– Stokes (URANS) computational fluid dynamics (CFD) solver with a computational structural dynamics (CSD) code to predict pitch/ plunge and parabolic camber flutter speeds of a thin symmetrical airfoil in incompressible and compressible flow is demonstrated in this work. This CFD/CSD method is believed to be one of the first approaches that includes full-surface morphing for rotating blades in the current published literature.