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• W1553885497 abstract "The technique of floating shock fitting is adapted to the computation of the inviscid flowfield about circular cones in a supersonic free stream at angles of attack that exceed the cone half-angle. The resulting equations are applicable over the complete range of free-stream Mach numbers, angles of attack and cone half-angles for which the bow shock is attached. A finite difference algorithm is used to obtain the solution by an unsteady relaxation approach. The bow shock, embedded cross-flow shock, and vortical singularity in the leeward symmetry plane are treated as floating discontinuities in a fixed computational mesh. Where possible, the flowfield is partitioned into windward, shoulder, and leeward regions with each region computed separately to achieve maximum computational efficiency. An alternative shock fitting technique which treats the bow shock as a computational boundary is developed and compared with the floating-fitting approach. Several surface boundary condition schemes are also analyzed." @default.
• W1553885497 created "2016-06-24" @default.
• W1553885497 creator A5007720279 @default.
• W1553885497 creator A5040159607 @default.
• W1553885497 creator A5062878558 @default.
• W1553885497 date "2018-08-13" @default.
• W1553885497 modified "2023-10-17" @default.
• W1553885497 title "Computation of the inviscid supersonic flow about cones at large angles of attack by a floating discontinuity approach" @default.
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• W1553885497 doi "https://doi.org/10.31274/rtd-180813-2617" @default.
• W1553885497 hasPublicationYear "2018" @default.
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