A Numerical Solution of Supersonic and Hypersonic Viscous Flow Fields Around Thin Planar Delta Wings.
AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO
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A numerical technique was used to compute the supersonic and hypersonic, viscous flow fields around thin planar delta wings. These solutions were obtained by solving the Navier-Stokes equations subject to a conical approximation. The integration technique used was the MacCormack finite-difference scheme. Solutions were obtained for the upper-only, lower-only, and total flow fields around delta wings with supersonic leading edges.
- Numerical Mathematics
- Fluid Mechanics