Hi,
two weeks ago Marshall Buhl informed that one should update to the current alpha-Version of WT_Perf. Today I did the update and I am having trouble with my airfolis now.
With the old version of WT_Perf I used the same Airfoil files as with FAST. If I try to do that with the current version, WT_Perf fails with
Angle of attack range of airfoil tables for segment #1 must be from -180 to 180.
However the echo-file of WT_Perf looks like this:
"AeroData\cylinder.dat"
FirstHead - First line in the airfoil file.
Round Root Section
File: WTCRound.dat
1 NumTabs - Number of airfoil tables for segment #1.
0.0000E+00 RnAry - Reynolds number values for the airfoil tables.
1.4000E+01 ASAry - Stall AoA for this airfoil table.
0.0 No longer used, enter zero
0.0 No longer used, enter zero
0.0 No longer used, enter zero
0.0000E+00 AOLAry - zero-lift AoA
0.0000E+00 CnAAry - Cn slope for zero lift
0.0000E+00 CnSAry - Cn at stall value for positive AoA
0.0000E+00 CnSLAry - Cn at stall value for negative AoA
0.0000E+00 AODAry - AoA for minimum Cd
1.0000E+00 CDOAry - minimum Cd value
-180.0000 0.0000 0.5000 0.0000
0.0000 0.0000 0.5000 0.0000
180.0000 0.0000 0.5000 0.0000
So in my opinion, WT_Perf does read the airfoil table and it contains angles of attack from -180 to 180. What is happening here?