Aerodynamic Analysis of AircraftA320

About this project

This aircraft simulation shows the airflow distribution around an aircraft design at low subsonic compressible flow regime.The flow of air around the commercial aircraft model was simulated via the Reynolds-averaged Napier-Stokes (RANS) method. The flow conditions were Mach number M 0.35, Angle of Attack 2 degrees, Pressure P 100000 pa and temperature T 0 degrees Celsius. For turbulence modeling, the k-omega SST model was used with the wall function approach. A ramping of the velocity boundary condition was applied up to the free stream value for better convergence.