Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca0008-il-100000 Airfoil,naca0008-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,34.5518 Max Cl/Cd alpha,3.75 Url,http://www.airfoiltools.com/polar/csv?polar=xf-naca0008-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.250,-0.5657,0.09227,0.08768,0.0037,1.0000,0.1506 -9.000,-0.5968,0.08657,0.08208,-0.0018,1.0000,0.1523 -8.750,-0.7155,0.08997,0.08534,0.0035,1.0000,0.1405 -8.500,-0.6980,0.08727,0.08260,0.0072,1.0000,0.1461 -7.750,-0.7635,0.05433,0.04844,-0.0150,1.0000,0.0842 -7.500,-0.7567,0.04621,0.03951,-0.0139,1.0000,0.0679 -7.250,-0.7443,0.04127,0.03418,-0.0129,1.0000,0.0666 -7.000,-0.7295,0.03756,0.02981,-0.0114,1.0000,0.0680 -6.750,-0.7128,0.03389,0.02551,-0.0100,1.0000,0.0699 -6.500,-0.6925,0.03043,0.02174,-0.0091,1.0000,0.0724 -6.250,-0.6698,0.02856,0.01967,-0.0083,1.0000,0.0788 -6.000,-0.6461,0.02650,0.01702,-0.0070,1.0000,0.0831 -5.750,-0.6224,0.02439,0.01495,-0.0065,1.0000,0.0906 -5.500,-0.5970,0.02293,0.01315,-0.0056,1.0000,0.0969 -5.250,-0.5724,0.02125,0.01153,-0.0050,1.0000,0.1045 -5.000,-0.5476,0.01991,0.01014,-0.0042,1.0000,0.1134 -4.750,-0.5232,0.01871,0.00893,-0.0032,1.0000,0.1233 -4.500,-0.5004,0.01744,0.00779,-0.0021,1.0000,0.1392 -4.250,-0.4799,0.01598,0.00669,-0.0008,1.0000,0.1789 -4.000,-0.4646,0.01393,0.00582,0.0010,1.0000,0.3548 -3.750,-0.4471,0.01294,0.00553,0.0032,1.0000,0.5049 -3.500,-0.4272,0.01239,0.00535,0.0054,1.0000,0.6034 -3.250,-0.4074,0.01201,0.00528,0.0080,1.0000,0.6924 -3.000,-0.3881,0.01184,0.00537,0.0114,1.0000,0.7806 -2.750,-0.3652,0.01191,0.00552,0.0144,1.0000,0.8508 -2.500,-0.3298,0.01214,0.00566,0.0147,1.0000,0.9037 -2.250,-0.2728,0.01247,0.00575,0.0102,1.0000,0.9441 -2.000,-0.1988,0.01262,0.00562,0.0015,1.0000,0.9717 -1.750,-0.1253,0.01247,0.00523,-0.0080,1.0000,0.9946 -1.500,-0.0917,0.01211,0.00478,-0.0103,1.0000,1.0000 -1.250,-0.0747,0.01182,0.00444,-0.0093,1.0000,1.0000 -1.000,-0.0582,0.01160,0.00418,-0.0080,1.0000,1.0000 -0.750,-0.0424,0.01144,0.00399,-0.0063,1.0000,1.0000 -0.500,-0.0276,0.01133,0.00387,-0.0044,1.0000,1.0000 -0.250,-0.0137,0.01126,0.00379,-0.0022,1.0000,1.0000 0.000,0.0000,0.01124,0.00377,0.0000,1.0000,1.0000 0.250,0.0137,0.01126,0.00379,0.0022,1.0000,1.0000 0.500,0.0276,0.01133,0.00387,0.0044,1.0000,1.0000 0.750,0.0424,0.01144,0.00399,0.0063,1.0000,1.0000 1.000,0.0582,0.01160,0.00418,0.0080,1.0000,1.0000 1.250,0.0748,0.01182,0.00444,0.0093,1.0000,1.0000 1.500,0.0917,0.01211,0.00478,0.0103,1.0000,1.0000 1.750,0.1253,0.01247,0.00523,0.0080,0.9946,1.0000 2.000,0.1988,0.01262,0.00562,-0.0015,0.9717,1.0000 2.250,0.2728,0.01247,0.00575,-0.0102,0.9441,1.0000 2.500,0.3298,0.01214,0.00566,-0.0147,0.9038,1.0000 2.750,0.3652,0.01191,0.00552,-0.0144,0.8509,1.0000 3.000,0.3881,0.01184,0.00537,-0.0114,0.7806,1.0000 3.250,0.4074,0.01201,0.00528,-0.0080,0.6924,1.0000 3.500,0.4273,0.01239,0.00535,-0.0054,0.6034,1.0000 3.750,0.4471,0.01294,0.00553,-0.0032,0.5049,1.0000 4.250,0.4799,0.01598,0.00669,0.0008,0.1789,1.0000 4.500,0.5004,0.01744,0.00779,0.0021,0.1392,1.0000 4.750,0.5232,0.01871,0.00893,0.0032,0.1233,1.0000 5.000,0.5476,0.01991,0.01014,0.0042,0.1134,1.0000 5.250,0.5724,0.02125,0.01153,0.0050,0.1045,1.0000 5.500,0.5970,0.02294,0.01315,0.0056,0.0969,1.0000 5.750,0.6224,0.02439,0.01495,0.0065,0.0906,1.0000 6.000,0.6461,0.02650,0.01703,0.0070,0.0831,1.0000 6.250,0.6698,0.02856,0.01967,0.0083,0.0788,1.0000 6.500,0.6925,0.03043,0.02174,0.0091,0.0724,1.0000 6.750,0.7128,0.03390,0.02552,0.0100,0.0699,1.0000 7.000,0.7295,0.03757,0.02982,0.0114,0.0680,1.0000 7.250,0.7443,0.04127,0.03418,0.0129,0.0666,1.0000 7.500,0.7567,0.04621,0.03951,0.0139,0.0679,1.0000 7.750,0.7636,0.05433,0.04843,0.0150,0.0842,1.0000 8.500,0.6984,0.08728,0.08262,-0.0073,0.1461,1.0000 8.750,0.7192,0.08972,0.08510,-0.0025,0.1403,1.0000 9.000,0.7106,0.09575,0.09106,-0.0062,0.1377,1.0000 9.250,0.5654,0.09211,0.08752,-0.0037,0.1507,1.0000