This script allows the optimisation of the angle attack of the blades and chord of the blades (using the Schmitz method).

The variables that can be changed for the optimisation of angle of attack are shown below.

real :: alpha
real :: tsr   
real :: radius
integer :: optimisationStations

Where; alpha is the angle of attack that the aerofoil performs best at, this value is in degrees, tsr is the tip speed ratio being optimised for, radius is the length of the blade in metres, and optimisationStations is the amount of sections the blade should be split into the optmise.

The variables that can be changed for the optimisation are shown below.

integer :: bladeNumber
character(len=20) :: fileName

Where; bladeNumber is the number of blades and fileName is the file name of the aerofoil polar for the blade, this polar must of the format shown in the example below.

  -5.000  -0.5702
  -4.750  -0.5472
  -4.500  -0.5014
  -4.250  -0.4879
  -4.000  -0.4684
  -3.750  -0.4281
  -3.500  -0.4129
  -3.250  -0.3693
  -3.000  -0.3623

Where; the left column is the angle of attack in degrees, and the right column is the coefficient of lift.

The optimise.f03 file is compiled using gfortran as shown in the below example.

gfortran optimise.f03 -o optimise

The output of the optimised blade geometry is in the dat file named output.dat. The format of the file is shown in the example below.

   0.060         31.5        0.121
   0.120         15.3        0.090
   0.180          8.9        0.067
   0.240          5.5        0.052
   0.300          3.4        0.042

The left column is the position along the blade in metres, the centre column is the optimised angle of attack of the blade in degrees and the right column is the optimised chord of the blade in metres. Each value takes up a width of 8. The space between values is 5.