Abstract:
A static aeroelastic computational module is developed on the flow solver TRIP. Firstly, the frame, main component units and coupling strategy of the static aeroelastic computational module are introduced briefly. Then numerical methods used in the component units are described in detail. Finally, the static aeroelastic computational module is tested and validated through three cases:high respect-ratio wing, DLR-F6 wing-body model and HIRENASD wing model. The computational results of high respect-ratio wing show that flexible matrix method, modal superposition method and finite element method can have same deformation results when the structure modes are selected properly. The result consistency of DLR-F6 or HIRENASD model among different solvers demonstrates that the static aeroelastic computational module has adopted a correct algorithm procedure. The results consistency of DLR-F6 or HIRENASD model between computations and tests shows that the present static aeroelastic computational module has a good prediction precision.