Compressible aerodynamics of a commercial aircraft
The flow of air around a commercial aircraft model is simulated via the Reynolds Averaged Navier-Stokes (RANS) method. The flow conditions are Mach number M = 0.35, Angle of Attack = 2 degreees, Pressure P = 100000 pa and temperature T = 0 degrees Celcius. For turbulence modeling the K-Omega SST model was used with wall function approach. A ramping of the velocity boundary condition was applied upto the free-stream value for better convergence.
The geometry is a simplified version of a commercial aircraft model provided by GrabCAD user Chao Wey.
The domain was meshed using the ‘Snappy-Hex-Mesh’ on the SimScale platform. The resulting mesh consists of approximately 6 million cells and is shown in the figure below.
The job was run on 32 compute cores and took less than 6 hours to complete. The simulation analysis the mean flow field and the pressure distribution around the aircraft. The results below (processed on ParaView) show significant compressibility effects by the changes in density.
The results give insight of the velocity field at different sections with the stream-lines and contours of Pressure distribution on the surface.