32nd AIAA Fluid Dynamics Conference and Exhibit · 2002 · 158 citations · 4 references
EngineeringAerospace EngineeringComputational EngineeringAerodynamicsComputational Fluid DynamicsFluid DynamicsAdaptive Mesh RefinementComputational AerodynamicsGrid AdaptationHypersonic AerodynamicsShock CapturingCfd SimulationComputational HypersonicsFlapsHypersonic FlowHypersonic Flow SimulationSmoothingTest CasesThermal Loads
The study evaluates the reliability of the unstructured TAU Code for hypersonic flows. The authors enhanced the TAU Code with residual smoothing, limiters, and adaptive time stepping, then validated it against European CFD solvers on canonical hyperboloid flare and wedge compression corner cases, and extended tests to a complex 3‑D configuration with deflected body flaps and adaptive mesh refinement to assess gap flow effects. Results demonstrate that the TAU‑Code reliably predicts complex cold hypersonic flows, though computational time remains a limitation.
The present investigation is aimed at evaluating the reliability of the unstructured TAU Code for hypersonic flows. To improve the efficiency, accuracy and robustness, the code has been modified concerning, for example, residual smoothing, limiters and timestep size to handle strong shocks. Validation was done using CFD solutions of different European CFD solvers for well known test cases such as hyperboloid flare. Further investigations have been done for wedge compression corners to study gap flow phenomena. Also, computations for a complex three dimensional configuration including deflected body flaps while considering the gap effect on the thermal loads have been performed. The effect of 3d adaptation has been intensively studied. The present investigation shows that the TAU-code is a reliable and efficient tool for complex cold hypersonic flow solutions, although its performance with respect to computing time should be improved.
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