To start off, a basic 2D NACA 4412 airfoil coordinates are derived from an online source and imported into STAR-CCM+ for appropriate modelling, meshing and setting up the boundary conditions. The coefficient of Lift, drag and moments are carefully observed, and flow behavior is understood from the velocity and pressure scalar scenes.
The geometry of 2D NACA 4412 airfoil is extruded and subtracted from a fluid domain to obtain a 3D domain containing a finite wing. The objective of this simulation is to analyze the flow around the wind and also study the wing tip vortex. The videos demonstrate how to use Iso-surfaces to understand the physics of the wing tip vortices.
The nature of the flow around the circular cylinder depends majorly on the Reynolds number and that is what is studied by carrying out the simulation. Steady and Unsteady turbulent flow in analyzed as demonstrated in the video series with focus on the von-karman vortex that can be measured using the Strouhal Number. The frequency of oscillation is calculated from the lift coefficient measured using a point probe.
This tutorial simulates two-dimensional, turbulent, compressible, transonic flow over an idealized airfoil. The freestream flow is subsonic, becoming supersonic on the suction side of the airfoil, and subsonic through a shock wave. The lift and drag coefficients are monitored to help determine whether convergence is reached. The final distribution of the pressure coefficient on the airfoil is then compared to experimental data.