Finned missile design entails accurate and computationally fast numerical techniques for predicting viscous flows over complex lifting configurations at small to moderate angles of attack and over Mach 3 to 15; these flows are often characterized by strong embedded shocks, so that numerical algorithms are also required to capture embedded shocks. The recent real-gas Flux Vector Splitting technique is here extended to investigate the Mach 3 flow over a typical finned missile configuration with/without side fin deflections. Elliptic grid-generation techniques for Mach 15 flows are shown to be inadequate for Mach 3 flows over finned configurations and need to be modified. Fin-deflection studies indicate that even small amounts of missile fin deflection can substantially modify vehicle aerodynamics. This 3D parabolized Navier-Stokes scheme is also extended into an efficient embedded algorithm for studying small axially separated flow regions due to strong fin and control surface deflections.
PNS predictions for supersonic/hypersonic flows over finned missile configurations
AIAA, Applied Aerodynamics Conference ; 1992 ; Palo Alto, CA, United States
1992-06-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Supersonic-Hypersonic Flowfield Predictions over Typical Finned Missile Configurations
Online Contents | 1993
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