############################################################ # UFR31 Flow Around (Airfoils and) Blades (Subsonic) # # File contains the static pressure coefficient # distribution along the blade # # Inlet Air Angle : 40.0deg # Inlet Mach Number : 0.25 # Total Pressure : 1.03Atm # Total Temperature : 294K # Reynolds number : 700000 ############################################################ %TA = 6 %UFR = 31 %Column1Name = Chordwise position %Column1Units = Non-dimensional with respect to chord %Column1Type = Real %Column2Name = Static pressure coefficient %Column2Units = Non-dimensional [ (p-p_in)/(0.5*rho*V_in*V_in) ] %Column2Type = Real %End of Metadata 2.230353e-02 3.747981e-01 4.400519e-02 4.426494e-01 7.522570e-02 3.651050e-01 1.124711e-01 3.602585e-01 1.812031e-01 4.135703e-01 2.558554e-01 4.862682e-01 3.401977e-01 5.008078e-01 4.087491e-01 4.620355e-01 4.792423e-01 4.135703e-01 5.577117e-01 4.329564e-01 6.381514e-01 4.571890e-01 7.107004e-01 4.571890e-01 7.871900e-01 4.668821e-01 8.303272e-01 4.668821e-01 8.636606e-01 4.668821e-01 9.086921e-01 4.329564e-01 9.576166e-01 3.844911e-01 9.612816e-01 2.536349e-01 9.082739e-01 2.197092e-01 8.631664e-01 2.148627e-01 8.278058e-01 1.809370e-01 7.846590e-01 1.760905e-01 7.138902e-01 8.400646e-02 6.352973e-01 1.615509e-03 5.566568e-01 -1.050081e-01 4.780164e-01 -2.116317e-01 4.072286e-01 -3.134087e-01 3.383446e-01 -4.442649e-01 2.577624e-01 -5.411955e-01 1.794735e-01 -4.684976e-01 1.108936e-01 -4.442649e-01 7.563749e-02 -4.248788e-01 4.227565e-02 -4.394184e-01 2.251576e-02 -5.169628e-01 1.640533e-02 -6.332795e-01