Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-sc20503-il-500000-n5 Airfoil,sc20503-il Reynolds number,500000 Ncrit,5 Mach,0 Max Cl/Cd,35.2537 Max Cl/Cd alpha,1.5 Url,http://airfoiltools.com/polar/csv?polar=xf-sc20503-il-500000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.6410,0.10227,0.09999,0.0177,1.0000,0.0052 -8.500,-0.6368,0.09832,0.09606,0.0156,1.0000,0.0052 -8.250,-0.6327,0.09437,0.09213,0.0133,1.0000,0.0052 -8.000,-0.6280,0.09030,0.08808,0.0104,1.0000,0.0052 -7.750,-0.6184,0.08557,0.08336,0.0053,1.0000,0.0052 -7.500,-0.6056,0.08032,0.07811,-0.0012,1.0000,0.0052 -7.250,-0.5908,0.07491,0.07266,-0.0075,1.0000,0.0052 -7.000,-0.5746,0.06961,0.06731,-0.0128,1.0000,0.0052 -6.750,-0.5569,0.06442,0.06204,-0.0174,1.0000,0.0052 -6.500,-0.5378,0.05935,0.05686,-0.0213,1.0000,0.0052 -6.250,-0.5188,0.05294,0.05033,-0.0255,1.0000,0.0053 -6.000,-0.4983,0.04617,0.04334,-0.0295,1.0000,0.0056 -5.750,-0.4747,0.04067,0.03761,-0.0323,1.0000,0.0058 -5.500,-0.4488,0.03598,0.03266,-0.0345,1.0000,0.0059 -5.250,-0.4210,0.03180,0.02819,-0.0362,1.0000,0.0061 -5.000,-0.3914,0.02796,0.02404,-0.0374,1.0000,0.0061 -4.500,-0.3328,0.02292,0.01849,-0.0385,1.0000,0.0049 -4.250,-0.3003,0.01892,0.01402,-0.0397,1.0000,0.0044 -4.000,-0.2686,0.01598,0.01064,-0.0403,1.0000,0.0041 -3.750,-0.2380,0.01359,0.00776,-0.0404,1.0000,0.0037 -3.500,-0.2081,0.01162,0.00552,-0.0404,1.0000,0.0035 -3.250,-0.1782,0.01008,0.00379,-0.0407,1.0000,0.0033 -3.000,-0.1479,0.00897,0.00253,-0.0412,1.0000,0.0034 -2.750,-0.1185,0.00831,0.00171,-0.0415,1.0000,0.0037 -2.500,-0.0904,0.00798,0.00126,-0.0415,1.0000,0.0045 -2.250,-0.0631,0.00777,0.00105,-0.0414,1.0000,0.0105 -2.000,-0.0309,0.00646,0.00084,-0.0435,1.0000,0.3233 -1.750,0.0000,0.00530,0.00086,-0.0450,1.0000,0.6723 -1.500,0.0264,0.00512,0.00090,-0.0446,1.0000,0.7486 -1.250,0.0526,0.00504,0.00091,-0.0442,1.0000,0.7788 -1.000,0.0786,0.00498,0.00094,-0.0438,1.0000,0.8043 -0.750,0.1048,0.00495,0.00097,-0.0434,1.0000,0.8240 -0.500,0.1308,0.00492,0.00102,-0.0429,1.0000,0.8396 -0.250,0.1569,0.00490,0.00109,-0.0425,1.0000,0.8542 0.250,0.2300,0.00714,0.00115,-0.0464,0.3111,0.8763 0.500,0.2537,0.00839,0.00136,-0.0462,0.0116,0.8892 0.750,0.2794,0.00855,0.00154,-0.0456,0.0044,0.9025 1.000,0.3044,0.00877,0.00191,-0.0448,0.0036,0.9190 1.500,0.3543,0.01005,0.00355,-0.0428,0.0032,1.0000 1.750,0.3815,0.01142,0.00507,-0.0423,0.0033,1.0000 2.000,0.4092,0.01320,0.00706,-0.0417,0.0035,1.0000 2.250,0.4376,0.01538,0.00953,-0.0410,0.0038,1.0000 2.500,0.4657,0.01785,0.01252,-0.0403,0.0041,1.0000 2.750,0.4932,0.02089,0.01596,-0.0395,0.0045,1.0000 3.000,0.5177,0.02530,0.02082,-0.0388,0.0052,1.0000 3.250,0.5464,0.02601,0.02165,-0.0382,0.0058,1.0000 3.500,0.5731,0.02916,0.02512,-0.0373,0.0060,1.0000 3.750,0.5980,0.03270,0.02896,-0.0367,0.0060,1.0000 4.000,0.6214,0.03653,0.03307,-0.0364,0.0058,1.0000 4.250,0.6432,0.04085,0.03765,-0.0363,0.0056,1.0000 4.500,0.6630,0.04602,0.04308,-0.0365,0.0054,1.0000 4.750,0.6796,0.05286,0.05019,-0.0374,0.0052,1.0000 5.000,0.6976,0.05849,0.05597,-0.0385,0.0051,1.0000 5.250,0.7160,0.06332,0.06095,-0.0398,0.0051,1.0000 5.500,0.7332,0.06827,0.06603,-0.0416,0.0051,1.0000 5.750,0.7490,0.07335,0.07121,-0.0439,0.0051,1.0000 6.000,0.7632,0.07849,0.07643,-0.0467,0.0051,1.0000 6.250,0.7759,0.08368,0.08170,-0.0500,0.0051,1.0000 6.500,0.7868,0.08888,0.08694,-0.0537,0.0051,1.0000 6.750,0.7959,0.09404,0.09214,-0.0578,0.0051,1.0000 7.000,0.8032,0.09913,0.09724,-0.0623,0.0051,1.0000 7.250,0.8061,0.10385,0.10196,-0.0664,0.0051,1.0000 7.500,0.8073,0.10829,0.10638,-0.0697,0.0051,1.0000 7.750,0.8090,0.11265,0.11073,-0.0722,0.0051,1.0000