A Boundary Integral Formulation for Unsteady Transonic Potential Flows,
ROME UNIV (ITALY)
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A boundary integral formulation for the analysis of unsteady potential transonic flows around airplanes is presented. The formulation is applied to steady and unsteady two-dimensional and three-dimensional configurations under the small-perturbation assumption. The results are compared with existing numerical andor experimental results, and demonstrate that the algorithm is capable of capturing shocks. However, the location predicted appears to be ahead of that predicted by conservative finite-difference schemes nonetheless, considering the preliminary nature of this work, the agreement obtained is quite satisfactory.
- Fluid Mechanics