To overcome the shortcomings of the schlieren visualization method, which is the difficulties in capturing the three-dimensional flow structures, the application of the computed tomography has been studied. This study aims to investigate the usefulness of this method for complicated flow structures in the wind tunnel. By applying this method to the flow field around a rocket-like slender body with a medium angle of attack in a supersonic flow, the following two issues were examined. The one is the influence of the shock waves reflected at the wind tunnel wall (especially the visualization windows). The results show that the artifacts caused by these shock waves can be reduced by using the buffer region in reconstruction. The other is the fine structures around the body. The results show that this method has enough resolution to capture the fine structures such as the vortices separated from the body, shock waves diffracted by the vortices, shock waves caused by the vortices, and complicated shock structures around protuberances. In particular, the reconstructed results show the asymmetry of the vortices due to the protuberances, suggesting that this method is useful for comparison with the numerical simulations.
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