Abstract.
The hypersonic intake problem is essentually subject to viscous complication, since boundary layers form under adverse steamwise pressure gradients. In addition boundary layers become thick underneath the forebody upsteam of the intake, and some boundary layer bleeding may be required - however, internal ducting would be hot and heavy, and boundary layers should thus be driven laterally towards intake corners, from which they can be dumped directly to external or underwing flows. In addition, unswept leading edges give rise to severe heating, and the design of intakes with all swept leading edges is of interest. At least at some design conditions, particular forms of allswept intakes permit the achievement of known crossflows in the boundary layer, and these controlled crossflows offer the prospect of reducing the demand for internal bleeds, subject to the acceptance of geometrical constraints for example on intake sweep and the extent of compression. Analysis and CFD are applied in this paper to the design of such compression surfaces for the viscous flow of a perfect and real gas - examples of application to intake-forebody and engine/airframe integration are presented.

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Last amended: Dec 2013