Novel method based on inflatable bump for vertical tail buffeting suppression

A study was conducted to generate a hybrid unstructured computational volume mesh, which was a prism element in boundary layer and a tetrahedron element in the other fluid zone. To simulate the complex vortices on the suction side of the delta wing as accurately as possible, mesh elements in the suction zone were refined adequately. Pressure far-field conditions were applied at far-field boundaries, no slip conditions were used at the wall, and it is assumed that the wall was rigid. A comparison was made between the computational and experimental results of the pressure coefficient of the VFE-2 surface to validate the current computational method.