Test for the updated version.

The newer code is tested for a configuration of 2n16p.
The run is supposed to reach t=60 with inflow turbulence.
Inflow turbulence set back to old version.
Add output on intermediate results saving.
Change nthick and nbody to 1

Also changed the informative output generated when saving intermediate
results.
New executable
Check out interpVar from sinaCode
Clcomputation first attempt

The computation is done in the module rpt. clComp computes area for the
blocks in contact with aerofoils and prints total area per block.
Area computation set up.

The results are not the ones expected and the area values are wrong.
Cl computation implemented

The subroutine calculates the area when mode=0. When mode=1
it computes the Cl value at each side of the selected aerofoil
saves it in different dat files.
Cl computation implemented version 2

This version computes the cl value and then sends the value to the 0
processor which is the one taking care of writing the values to files.
Lift integration sign changed.

The pressure points down in the suction surface and up in the pressure
surface, so the sign should be reverted in the equation.
Change output format on screen and on cl files
walltime changed
Cl calculation changed.

The normals should point the inside of the aerofoil not the outsite.
Also for the computation of the Cl the lift force has to be divided by
the dynamic pressure times the surface. The dynamic pressure is computed
with the mach number given from the input, not from the moving frame
velocity, hence remains constant.
Cl computation updated.

The sending and receive strategy was wrong. The master of each block is
now always involved in the calculation, i.e. it is touching the aerofoil
surface. The Cl was too high because only the force of the upper side
was being computed.
ignoring files
Merge branch 'clDevelopment'
change input files
change input file
fixed ignored files