Supersonic flow past circular cones at high angles of yaw, downstream of separation
The calculation of viscous supersonic flow over circular cones at high angles of yaw was partially carried out by Fletcher and Holt (1976) and by Holt and Chan (1979). The flow field was calculated as the interaction between the outer inviscid flow and an inner conical boundary layer flow. The latter was treated by the orthonormal version of the Method of Integral Relations (M.I.R.) (Fletcher and Holt, 1975) and continued up to the cross flow separation line.
The present work deals with the boundary layer downstream of this separation line where the circumferential velocity component, w, is reversed. The orthonormal version of M.I.R. needs to be modified in this region to take account of a minimum point in w near the cone surface. In contrast to two-dimensional flow, this can be achieved by using polynomials to represent the normal gradient of w as a function of w, and square root factors, which seriously complicate the use of orthonormal M.I.R., are not needed. The extended calculation enables us to calculate the complete flow field over yawed supersonic cones, at different Mach numbers and yaw angles, including that in the far leeward region.
KeywordsSupersonic Flow Circular Cone Displacement Thickness Supersonic Boundary Layer Boundary Layer Behavior
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