A numerical finite-volume method is proposed for solving the Euler equations of a steady three-dimensional flow. The subsonic regions embedded in steady supersonic flow about aircraft are computed by introducing a time-dependent coordinate system that maps the fuselage and wing into one coordinate surface. The suitability of the method to a delta-winged aircraft is demonstrated, and its applicability to rectangular-winged aircraft and problems in internal transonic flow is pointed out.
Finite-volume solution of the Euler equations for steady three-dimensional transonic flow
International Conference on Numerical Methods in Fluid Dynamics ; 1976 ; Enschede, Netherlands
1976-01-01
Miscellaneous
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English