Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-sc20706-il-100000-n5 Airfoil,sc20706-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,33.2586 Max Cl/Cd alpha,1.25 Url,http://airfoiltools.com/polar/csv?polar=xf-sc20706-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.6050,0.07650,0.07146,-0.0288,1.0000,0.0264 -8.750,-0.6062,0.07127,0.06620,-0.0326,1.0000,0.0259 -8.500,-0.6052,0.06594,0.06080,-0.0361,1.0000,0.0255 -8.250,-0.6006,0.06054,0.05525,-0.0396,1.0000,0.0251 -8.000,-0.5916,0.05503,0.04952,-0.0430,1.0000,0.0247 -7.750,-0.5774,0.04950,0.04366,-0.0463,1.0000,0.0244 -7.500,-0.5578,0.04405,0.03779,-0.0496,1.0000,0.0242 -7.250,-0.5331,0.03894,0.03214,-0.0526,1.0000,0.0242 -7.000,-0.5044,0.03457,0.02714,-0.0552,1.0000,0.0251 -6.750,-0.4736,0.03162,0.02348,-0.0570,1.0000,0.0271 -6.500,-0.4440,0.02784,0.01918,-0.0590,1.0000,0.0281 -6.250,-0.4148,0.02529,0.01626,-0.0599,1.0000,0.0288 -6.000,-0.3861,0.02328,0.01397,-0.0605,1.0000,0.0299 -5.750,-0.3578,0.02161,0.01209,-0.0607,1.0000,0.0316 -5.500,-0.3294,0.02017,0.01049,-0.0609,1.0000,0.0339 -5.250,-0.3012,0.01919,0.00933,-0.0611,1.0000,0.0391 -5.000,-0.2713,0.01793,0.00805,-0.0621,1.0000,0.0449 -4.750,-0.2405,0.01699,0.00700,-0.0630,1.0000,0.0529 -4.500,-0.2088,0.01613,0.00614,-0.0642,1.0000,0.0682 -4.250,-0.1752,0.01518,0.00533,-0.0659,1.0000,0.1063 -4.000,-0.1336,0.01317,0.00481,-0.0708,1.0000,0.4186 -3.750,-0.1087,0.01283,0.00511,-0.0697,1.0000,0.6113 -3.500,-0.0863,0.01293,0.00530,-0.0679,1.0000,0.6765 -3.250,-0.0655,0.01309,0.00548,-0.0657,1.0000,0.7186 -3.000,-0.0450,0.01323,0.00561,-0.0634,1.0000,0.7483 -2.500,-0.0005,0.01336,0.00563,-0.0603,1.0000,0.7868 -2.250,0.0237,0.01337,0.00560,-0.0593,1.0000,0.8002 -2.000,0.0498,0.01336,0.00555,-0.0590,1.0000,0.8116 -1.750,0.0739,0.01334,0.00553,-0.0582,1.0000,0.8212 -1.500,0.0993,0.01332,0.00550,-0.0577,1.0000,0.8305 -1.250,0.1256,0.01332,0.00551,-0.0574,1.0000,0.8404 -1.000,0.1517,0.01332,0.00554,-0.0572,1.0000,0.8500 -0.750,0.1769,0.01330,0.00558,-0.0566,1.0000,0.8587 -0.500,0.2031,0.01332,0.00567,-0.0565,1.0000,0.8680 -0.250,0.2289,0.01333,0.00578,-0.0561,1.0000,0.8782 0.000,0.2530,0.01333,0.00588,-0.0555,1.0000,0.8882 0.250,0.2778,0.01334,0.00603,-0.0550,1.0000,0.8987 0.500,0.3027,0.01336,0.00620,-0.0545,1.0000,0.9099 0.750,0.3266,0.01337,0.00642,-0.0539,1.0000,0.9226 1.000,0.3495,0.01337,0.00662,-0.0530,1.0000,0.9374 1.250,0.4154,0.01249,0.00606,-0.0597,0.9158,0.9387 1.500,0.4920,0.01518,0.00552,-0.0677,0.1377,0.9357 1.750,0.5139,0.01616,0.00610,-0.0666,0.0733,0.9487 2.000,0.5385,0.01690,0.00691,-0.0658,0.0586,0.9660 2.250,0.5666,0.01774,0.00778,-0.0660,0.0464,1.0000 2.500,0.5954,0.01886,0.00901,-0.0663,0.0406,1.0000 2.750,0.6233,0.02053,0.01067,-0.0666,0.0359,1.0000 3.000,0.6538,0.02160,0.01196,-0.0670,0.0314,1.0000 3.250,0.6839,0.02333,0.01386,-0.0673,0.0293,1.0000 3.500,0.7140,0.02528,0.01605,-0.0676,0.0279,1.0000 3.750,0.7431,0.02752,0.01859,-0.0676,0.0270,1.0000 4.000,0.7709,0.03009,0.02155,-0.0675,0.0265,1.0000 4.250,0.7968,0.03305,0.02504,-0.0670,0.0262,1.0000 4.500,0.8195,0.03633,0.02873,-0.0665,0.0253,1.0000 4.750,0.8396,0.04010,0.03310,-0.0654,0.0237,1.0000 5.000,0.8595,0.04392,0.03751,-0.0641,0.0228,1.0000 5.250,0.8757,0.04841,0.04248,-0.0629,0.0228,1.0000 5.500,0.8892,0.05316,0.04766,-0.0619,0.0229,1.0000 5.750,0.9001,0.05810,0.05296,-0.0610,0.0232,1.0000 6.000,0.9082,0.06320,0.05835,-0.0604,0.0235,1.0000 6.250,0.9132,0.06842,0.06380,-0.0599,0.0239,1.0000 6.500,0.9172,0.07343,0.06895,-0.0596,0.0247,1.0000 6.750,0.9156,0.08301,0.07908,-0.0624,0.0293,1.0000 7.000,0.9113,0.08919,0.08537,-0.0645,0.0312,1.0000 7.250,0.9054,0.09458,0.09080,-0.0661,0.0329,1.0000 7.750,0.7570,0.09697,0.09336,-0.0584,0.0296,1.0000 8.000,0.7472,0.10301,0.09937,-0.0611,0.0308,1.0000