Numerical Experiments with Hypersonic Flows Beneath a Cone-Delta-Wing Combination,
GLASGOW UNIV (UNITED KINGDOM) DEPT OF AERONAUTICS AND FLUID MECHANICS
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Numerical experiments of hypersonic flows beneath a cone-delta-wing combination have been carried out by solving the compressible Navier-Stokes equations using an assumption of local conicity. An implicit method is combined with a multigrid scheme in the solution procedure further insight into the complex flow structures due to interaction between the cone shock and the wing shock and the interaction of the resulting flow with the wing or cone boundary layer. Flow field pictures reveal phenomena of value in the design of hypersonic lifting vehicles, such as the interference pressure and the high local wall heating. Comparisons with experimental data and conical Euler solution are also made.
- Fluid Mechanics