First steps in Aerodynamics
with CFX TASCflow
IV. Supersonic flow
A initial Mach 2 flow is going to be simulated in this part, using as initial guess the solution of the Mach 0.8 flow. Two scheme will be checked : the modified linear profile scheme and the upwind difference scheme, which is one of the most basic ones.
1. Modified linear profile
The modified linear profile is a scheme based on the finite volume method, but the calculation of the transfers
are complicated because of an other fragmentation of the basic volume element. We will check the ability of this scheme
to solve a shock wave : meshes number of the shock repartition and quality of the shock description.
2. Upwind differences
The first difference it's possible to show between the two schemes is that the calculation with the upwind differences
are really longer than the previous ones, as the residuals evolution graph proofs.