# Solution to 3D Standard Configuration 10.
# Subsonic test case.
# Inlet Mach number: 0.7
# Inlet Flow Angle: 55 degrees
# Mode Shape: pitching
# Reduced frequency (full chord): 0.5
# Solution calculated by TurboSolve.x
# Number of Cells: 455988
# Variables: interblade phase-angle, aero. damping
0.000000 1.147538e-01
15.000000 2.489244e-02
30.000000 -3.469056e-02
45.000000 -8.194237e-02
60.000000 -1.340868e-01
75.000000 -2.020403e-01
90.000000 -2.750878e-01
105.000000 -3.392571e-01
120.000000 -3.819922e-01
135.000000 -3.895973e-01
150.000000 -3.480317e-01
165.000000 -2.492791e-01
180.000000 -9.585251e-02
195.000000 1.006427e-01
210.000000 3.193449e-01
225.000000 5.201296e-01
240.000000 6.450678e-01
255.000000 6.639244e-01
270.000000 6.083027e-01
285.000000 5.303432e-01
300.000000 4.614658e-01
315.000000 4.108418e-01
330.000000 3.608420e-01
345.000000 2.531123e-01
360.000000 1.147538e-01