Modeling the Benchmark Active Controls Wing Through Linear and Computational Aer oelastic Analyses

摘要

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 errors are generally less than those present in the small reported number of similar simulation attempts. An examination of the reasons for the underprediction of the transonic dip has not supported a previous hypothesis, but has shown some evidence for an alternative: namely, that the principal problem is overprediction of shock wave strength. This work has shown the importance of experimental validation in gaining insight into the fundamental performance of coupled codes, because a simulation code that performs adequately on the usual test cases has, like other codes before, struggled on this apparently simpler test case. However, due to certain aspects of the design of the wing (particularly, its small aspect ratio and all-moving surface), the BACT wing has proved to be a demanding test. Work continues in improving the aerodynamic solution and understanding the mechanisms of transonic flutter.