Modeling the benchmark active controls wing through linear and computational aeroelastic analyses

Advanced computational aeroelastic (CAE) methods allow both the structure and aerodynamics to be modeled through nonlinear equations, increasing model fidelity, although at a far higher cost in terms of CPU time than traditional linear schemes. The AGARD445.6 wing has been simulated by a large number of workers, generating results with good accuracy. A linearized model of the benchmark active controls (BACT) wing was developed and successfully used as the basis for a wide range of control law derivations. A moving mesh coupled code USCRANSMB was applied to the BACT wing test case, although the size and Mach range of the transonic dip are underpredicted and high subsonic flutter speeds are overpredicted. The importance of experimental validation in gaining insight into the fundamental performance of coupled codes that performs adequately on the usual test cases has also been discussed.