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Efficiency of boundary layer bleeding for hypersonic aircraft with ventral ramjet module

Among configurations studied for promising hypersonic airbreathing-engine-powered vehicles of different application, such configurations are usual whose powerplant units are designed in the form of a box-like engine module (nacelle) located under the wing or the lifting body. In such a configuration, the lower surface of the forebody is simultaneously the inlet-precompression surface. A thick boundary layer that develops on this surface and enters the inlet can significantly worsen the inlet and engine performance. This adverse effect can be decreased, for example, by mounting the inlet above the boundary layer using some bleed wedges. At the same time, it is obvious that the bleed wedges lead to a certain increase of the drag of the vehicle. This means that the total efficiency of such a boundary layer bleeding is determined by the compromise between the increase of the drag and the improvement of the internal characteristics of the inlet and the engine depending on the bleed wedge height. Very few papers are known which consider such issues as applied to hypersonic aircraft.