Applications of AUSM+ Scheme on Subsonic, Supersonic and Hypersonic Flows Fields

The performance of Advection Upstream Splitting Method AUSM schemes are evaluated against experimental flow fields at different Mach numbers and results are compared with experimental data of subsonic, supersonic and hypersonic flow fields. The turbulent model used here is SST model by Menter. The numerical predictions include lift coefficient, drag coefficient and pitching moment coefficient at different mach numbers and angle of attacks. This work describes a computational study undertaken to compute the Aerodynamic characteristics of different air vehicles configurations using a structured Navier-Stokes computational technique. The CFD code bases on the idea of upwind scheme for the convective (convective-moving) fluxes. CFD results for GLC305 airfoil and cone cylinder tail fined missile calculated on above mentioned turbulence model are compared with the available data. Wide ranges of Mach number from subsonic to hypersonic speeds are simulated and results are compared. When the computation is done by using viscous turbulence model the above mentioned coefficients have a very good agreement with the experimental values. AUSM scheme is very efficient in the regions of very high pressure gradients like shock waves and discontinuities. The AUSM versions simulate the all types of flows from lower subsonic to hypersonic flow without oscillations.

Authors:

• Muhammad Yamin Younis
• Muhammad Amjad Sohail
• Tawfiqur Rahman
• Zaka Muhammad
• Saifur Rahman Bakaul

Keywords:

• Subsonic
• supersonic
• Hypersonic
• AUSM+
• Drag Coefficient
• lift Coefficient
• Pitching moment coefficient
• pressure Coefficient
• turbulent flow.

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