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Computational aerodynamics offers one of the most promising means of improving the productivity of the aircraft design process. Evaluation of numerous geometric modifications in a typical design cycle is very costly and time consuming if done using wind tunnels alone. The potential-flow computational methods can provide reliable aerodynamic data needed for aircraft design as long as the flow is entirely subsonic or supersonic and remains attached. Methods based on the Euler and Navier-Stokes equations do not suffer from such restrictions and are, therefore, capable of providing aerodynamic data for a much wider range of flow conditions. Such capabilities are illustrated in this paper. Solutions obtained using a state-of-the-art Three-dimensional Euler/Navier-Stokes Aerodynamic Method, TEAM, are presented for four test cases ranging from an airfoil to the complete advanced tactical fighter prototype configuration.

Capabilities of the Three-dimensional Euler Aerodynamic Method (TEAM) for simulating nonlinear aerodynamics associated with transonic flows and leading-edge vortex flows are assessed. TEAM is based on a cell-centered finite-volume, multistage time-stepping algorithm. It accommodates patched zonal grids of arbitrary topologies with matched as well as mismatched grid distributions at the interfaces. Its ability to handle complex geometries, robustness, accuracy, and parametric sensitivity are used as the assessment criteria. Sensitivity of solutions to three numerical dissipation schemes and grid-density variations is investigated. Transonic-flow solutions for NLR 7301 airfoil, Wing C, and a canard-wing-body, and low-speed leading-edge vortex-flow solutions for a delta wing, a cropped-delta wing, and a double-delta wing-body are presented. The solutions are correlated with experimental data and other numerical solutions as applicable.