Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-sc20610-il-1000000 Airfoil,sc20610-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,74.2537 Max Cl/Cd alpha,5.25 Url,http://airfoiltools.com/polar/csv?polar=xf-sc20610-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr 0.250,0.4575,0.00647,0.00203,-0.1046,0.6165,0.6993 0.500,0.4804,0.00739,0.00229,-0.1037,0.4539,0.7025 0.750,0.5052,0.00814,0.00251,-0.1033,0.3270,0.7052 1.000,0.5309,0.00870,0.00269,-0.1030,0.2297,0.7080 1.250,0.5573,0.00916,0.00288,-0.1028,0.1605,0.7099 1.500,0.5842,0.00954,0.00307,-0.1027,0.1172,0.7119 1.750,0.6117,0.00983,0.00324,-0.1026,0.0908,0.7141 2.000,0.6393,0.01010,0.00342,-0.1025,0.0742,0.7163 2.250,0.6673,0.01031,0.00359,-0.1024,0.0653,0.7186 2.500,0.6951,0.01056,0.00379,-0.1024,0.0578,0.7206 2.750,0.7232,0.01075,0.00395,-0.1023,0.0533,0.7224 3.000,0.7506,0.01099,0.00418,-0.1022,0.0480,0.7246 3.250,0.7785,0.01115,0.00436,-0.1021,0.0451,0.7266 3.500,0.8057,0.01143,0.00461,-0.1019,0.0408,0.7287 3.750,0.8332,0.01164,0.00484,-0.1018,0.0382,0.7311 4.000,0.8605,0.01188,0.00506,-0.1016,0.0351,0.7334 4.250,0.8876,0.01219,0.00537,-0.1014,0.0320,0.7356 4.500,0.9150,0.01243,0.00560,-0.1012,0.0293,0.7376 4.750,0.9416,0.01281,0.00597,-0.1009,0.0266,0.7395 5.000,0.9686,0.01305,0.00624,-0.1007,0.0249,0.7418 5.250,0.9950,0.01340,0.00658,-0.1003,0.0233,0.7439 5.500,1.0205,0.01390,0.00712,-0.0998,0.0219,0.7459 5.750,1.0469,0.01423,0.00750,-0.0994,0.0212,0.7482 6.000,1.0730,0.01460,0.00790,-0.0990,0.0204,0.7506 6.250,1.0989,0.01499,0.00832,-0.0986,0.0197,0.7530 6.500,1.1244,0.01546,0.00880,-0.0981,0.0191,0.7551 6.750,1.1483,0.01614,0.00954,-0.0973,0.0184,0.7573 7.000,1.1715,0.01694,0.01042,-0.0964,0.0179,0.7595 7.250,1.1964,0.01740,0.01095,-0.0958,0.0177,0.7616 7.500,1.2211,0.01791,0.01153,-0.0952,0.0174,0.7639 7.750,1.2456,0.01841,0.01210,-0.0945,0.0170,0.7662 8.000,1.2697,0.01898,0.01272,-0.0938,0.0166,0.7686 8.250,1.2933,0.01959,0.01339,-0.0930,0.0163,0.7707 8.500,1.3166,0.02022,0.01409,-0.0922,0.0159,0.7729 8.750,1.3393,0.02087,0.01482,-0.0913,0.0157,0.7752 9.000,1.3613,0.02159,0.01561,-0.0903,0.0154,0.7773 9.250,1.3821,0.02248,0.01658,-0.0892,0.0151,0.7796 9.500,1.4006,0.02372,0.01793,-0.0877,0.0148,0.7819 9.750,1.4139,0.02584,0.02026,-0.0855,0.0145,0.7842 10.000,1.4306,0.02727,0.02185,-0.0837,0.0144,0.7863 10.250,1.4488,0.02827,0.02299,-0.0823,0.0143,0.7885 10.500,1.4658,0.02935,0.02421,-0.0806,0.0142,0.7907 10.750,1.4811,0.03056,0.02558,-0.0787,0.0141,0.7929 11.000,1.4943,0.03194,0.02712,-0.0766,0.0140,0.7952 11.250,1.5055,0.03343,0.02878,-0.0743,0.0139,0.7977 11.500,1.5150,0.03492,0.03043,-0.0718,0.0138,0.8001 11.750,1.5224,0.03643,0.03209,-0.0690,0.0136,0.8022 12.000,1.5252,0.03795,0.03377,-0.0656,0.0134,0.8049 12.250,1.5215,0.03949,0.03547,-0.0612,0.0133,0.8074 12.500,1.5177,0.04138,0.03753,-0.0573,0.0132,0.8099 12.750,1.5120,0.04358,0.03989,-0.0538,0.0131,0.8124 13.000,1.5017,0.04639,0.04288,-0.0506,0.0131,0.8148 13.250,1.4906,0.04950,0.04617,-0.0480,0.0130,0.8168 13.500,1.4758,0.05331,0.05017,-0.0463,0.0129,0.8191