Abstract
Steady, unsteady, and aeroelastic computations are performed on an advanced transonic wing configuration. The flow is modeled by the Navier-Stokes equations, and structures for aeroelastic computations are modeled by the modal equations. The inadequacy of Euler equations and the importance of using the Navier-Stokes equations with a turbulence model is demonstrated for supercritical flows in the transonic regime. The effect of Mach number on steady pressure distributions is illustrated. Steady flow computations for transonic wings are compared with wind-tunnel data and also with equivalent conventional wings. Unsteady computations are made hi the context of demonstrating the use of the indicial approach for generating aerodynamic data for aeroelastic computations. By using the unsteady data generated by indicial responses, a computationally efficient approach of computing preliminary flutter boundaries is demonstrated. The effect of Mach number on the flutter boundary including the prediction of the transonic flutter speed dip is demonstrated. The flutter boundaries of transonic wings are compared with equivalent conventional wings. Characteristics of the flutter boundaries are correlated with aerodynamic flow characteristics.
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