deltaStar was not recomputed for the transition point after averaging solutions, leading to oscillations in the transition region. Test cases have been updated accordingly and deltaStar computation is now tested in the 2D subsonic test case

+ Refactor adjoint and api's

Change potential and mesh derivatives to analytical. Also changed the residuals computation of the viscous solver to the analytical expression instead of solving the linear system. This commit reduces the computational cost of the coupled adjoint methodology by a factor 4, at least.

The api features 3 components: The solver, the geometry and the initial mesh. The api is tested in a aerodynamic shape case where the NACA0012 is constrained at 0deg AoA with cl=0.40 and the objective function to minimize is the drag wrt the max camber and the max camber position. The test case ends with a final shape close to the NACA4412 (camber = 35% & max camber pos = 41%)

Friction drag is now part of the implementation. The rhs of the adjoint system is updated and the test uses total drag. The adjoint test now uses the mesh update capability.

New surface mesh is imposed in the viscous solver in 2D and stagnation point is recomputed at the first coupling iteration

Added adjoint for AoA and mesh in 2D. Nodes indices are now passed to the BoundaryLayer object

Cp is not written since VTK changed the name of their function. Writting cp slices works with VTK 9.3.0

Increased number of elements in the TE region and updated tests values.

Adjoint is not working because the delta star box is missing

Boundary layer c++ objects are created in python with swig and are manipulated by the interface. The initial condition of the viscous solver was changed. All test cases have been adapted. A decrease in the number of iterations is globally observed. Results are slightly improved especially for the RAE validation case.

Validate 2D transonic capabilities.

Driver now computes the average position of the transition

DDicretization now throws a runtime error if the mesh size is < 2 elements.

Dart interface is now able to write the surface pressure distribution.

Adding scipy before script

Added test case on the rae2822 3D finite wing thattests the 3D functionnalities of the code with vtk writing

Added vtk support in Dart api. Modified writing of boundary layer slices and introduced new argument of blast - writeSlices - which indicates vtk where to extract cps. The feature is not yet available for the boundary layer slices as this would require interpolation in the viscous solver.

dart module is added to the python path and can be imported when running test cases

Modified CMakeLists.txt files to find amfe in dartflo subdirectory and linked dart, tbox and fwk libs with blast through swig. Changed root run.py file to find amfe.

Added the script, the lfs mesh for the inviscid calculation and the geo file to generate the viscous (structured) surface mesh. Minor changes in the interfaces, in particular associating different names to the different sections if needed.

Fixed API, dart interface and prevented segfault if the number of sections is not imposed correctly.