Abstract
Separation due to the shock wave/boundary layer interactions in a hypersonic inlet always brings negative effects on its performance. Thus, the three-dimensional characteristics and control method of shock/boundary layer interactions in a duct with finite width are investigated by both experimental and computational methods. Firstly, the uncontrolled cases, including the unseparated state and the separated state, are studied. The results show that the shock/boundary layer interactions generate complex three-dimensional flow structures, which will substantially deteriorate the performance of a hypersonic inlet. Then, the influence of a two-dimensional bump is obtained, which indicates that the shockinduced flow separation can be effectively reduced under the control of the bump.
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