摘要：Viscous and non-viscous supersonic flow simulations over a wing-body configuration are presented in this work. The numerical analysis is carried out using the Finite Element Method with an explicit one-step Taylor-Galerkin scheme and adaptive unstructured meshes employing linear tetrahedral elements. The calculations are performed with different Mach numbers (M = 2.3 and 4.63) and angles of attack (alpha = 6.2 deg and 11.1 deg). Finally, the structure of the flow field is discussed for each case and computational results are compared to available experimental data.
