################################################################### # #exp12.dat #TA6 Turbomachinery Internal Flows AC12 Steam Turbine Rotor Cascade # #Experimental results #Pressure distribution on the suction and pressure sides # #Relevant parameters #Inlet flow angle : beta1 = 70.7 deg #Incidence : i = 0 deg #Inlet Mach number : M1 = 0.375 #Isentropic exit Mach number : M2is = 1.198 #Reynolds number for exit velocity: Re2is = 1.48 x 10^6 #Kinetic energy loss coefficient : theta = 4.6% #Exit flow angle : beta2 = 29.8 deg #Total inlet pressure : p01 = 98071.7 Pa #Total inlet temperature : T01 = 289.65 K ################################################################### %AC = 6-12 %Column1Name = x/b %Column1Units = non-dimensional %Column1Type = real %Column2Name = p/p0 %Column2Units = non-dimensional %Column2Type = real %End Of Metadata 0.00485164 1.00509 -0.00422802 0.975524 -0.0066166 0.931241 -0.00845835 0.857446 -0.00154854 0.830922 -0.00766544 0.814656 0.00887085 0.788183 0.135273 0.720987 0.255285 0.65228 0.327082 0.587739 0.408451 0.526201 0.460968 0.463031 0.506548 0.427862 0.544397 0.463483 0.557014 0.475357 0.601937 0.475601 0.621409 0.463901 0.680234 0.406668 0.729378 0.352334 0.794594 0.296611 0.817138 0.292306 0.836309 0.296837 0.882008 0.428421 0.965601 0.42002 1.02283 0.275713 1.00218 0.350861 0.985073 0.40832 0.966842 0.526276 0.900314 0.652825 0.847687 0.721897 0.746929 0.790708 0.61729 0.859362 0.420185 0.932078 0.349317 0.946451 0.281658 0.960841 0.153005 0.976376 0.0500486 0.990575