Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-sc20402-il-200000-n5 Airfoil,sc20402-il Reynolds number,200000 Ncrit,5 Mach,0 Max Cl/Cd,40.107 Max Cl/Cd alpha,2.75 Url,http://airfoiltools.com/polar/csv?polar=xf-sc20402-il-200000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.750,-0.7033,0.12422,0.12080,0.0401,1.0000,0.0105 -9.500,-0.6994,0.12038,0.11698,0.0385,1.0000,0.0110 -9.250,-0.6956,0.11652,0.11314,0.0369,1.0000,0.0113 -9.000,-0.6917,0.11267,0.10931,0.0352,1.0000,0.0116 -8.750,-0.6878,0.10884,0.10551,0.0334,1.0000,0.0119 -8.500,-0.6839,0.10502,0.10172,0.0314,1.0000,0.0122 -8.250,-0.6799,0.10121,0.09794,0.0294,1.0000,0.0125 -8.000,-0.6759,0.09740,0.09416,0.0271,1.0000,0.0128 -7.750,-0.6713,0.09353,0.09032,0.0244,1.0000,0.0130 -7.500,-0.6629,0.08923,0.08604,0.0201,1.0000,0.0134 -7.250,-0.6512,0.08456,0.08137,0.0146,1.0000,0.0138 -7.000,-0.6362,0.07963,0.07642,0.0084,1.0000,0.0142 -6.750,-0.6174,0.07460,0.07134,0.0020,1.0000,0.0147 -6.500,-0.5940,0.06969,0.06633,-0.0044,1.0000,0.0153 -6.250,-0.5674,0.06520,0.06167,-0.0099,1.0000,0.0158 -6.000,-0.5425,0.06097,0.05726,-0.0135,1.0000,0.0161 -5.750,-0.5170,0.05673,0.05234,-0.0166,1.0000,0.0163 -5.500,-0.4921,0.05261,0.04798,-0.0190,1.0000,0.0164 -5.250,-0.4739,0.04468,0.03986,-0.0229,1.0000,0.0175 -5.000,-0.4532,0.04035,0.03542,-0.0249,1.0000,0.0193 -4.750,-0.4267,0.03675,0.03157,-0.0266,1.0000,0.0216 -4.500,-0.3970,0.03342,0.02791,-0.0280,1.0000,0.0247 -4.250,-0.3615,0.03356,0.02740,-0.0275,1.0000,0.0288 -4.000,-0.3362,0.02691,0.02059,-0.0302,1.0000,0.0322 -3.750,-0.3069,0.02431,0.01770,-0.0308,1.0000,0.0355 -3.500,-0.2746,0.02174,0.01468,-0.0305,1.0000,0.0251 -3.250,-0.2428,0.01906,0.01158,-0.0300,1.0000,0.0130 -3.000,-0.2128,0.01682,0.00898,-0.0298,1.0000,0.0102 -2.750,-0.1834,0.01505,0.00690,-0.0293,1.0000,0.0083 -2.500,-0.1551,0.01394,0.00563,-0.0289,1.0000,0.0072 -2.250,-0.1273,0.01298,0.00459,-0.0287,1.0000,0.0070 -1.500,-0.0398,0.00990,0.00105,-0.0291,1.0000,0.0086 -1.250,-0.0296,0.00668,0.00100,-0.0255,1.0000,0.8860 -1.000,-0.0077,0.00641,0.00073,-0.0236,1.0000,1.0000 -0.750,0.0202,0.00642,0.00065,-0.0237,1.0000,1.0000 -0.500,0.0478,0.00643,0.00062,-0.0238,1.0000,1.0000 -0.250,0.0754,0.00644,0.00064,-0.0238,1.0000,1.0000 0.250,0.1513,0.00769,0.00084,-0.0274,0.5534,1.0000 0.500,0.1729,0.01019,0.00142,-0.0271,0.0074,1.0000 1.250,0.2555,0.01347,0.00505,-0.0261,0.0069,1.0000 1.500,0.2833,0.01443,0.00610,-0.0258,0.0074,1.0000 1.750,0.3118,0.01574,0.00760,-0.0252,0.0087,1.0000 2.000,0.3409,0.01765,0.00984,-0.0245,0.0109,1.0000 2.250,0.3696,0.02004,0.01258,-0.0239,0.0139,1.0000 2.750,0.4123,0.01028,0.00408,-0.0189,0.0356,1.0000 4.000,0.5325,0.02413,0.01957,-0.0180,0.0198,1.0000 4.250,0.5507,0.02819,0.02378,-0.0185,0.0180,1.0000 4.500,0.5973,0.05219,0.04754,-0.0245,0.0163,1.0000 6.750,0.7782,0.09252,0.08967,-0.0538,0.0123,1.0000 7.000,0.7864,0.09732,0.09447,-0.0584,0.0121,1.0000 7.250,0.7907,0.10174,0.09887,-0.0623,0.0119,1.0000 7.500,0.7931,0.10592,0.10303,-0.0651,0.0116,1.0000 7.750,0.7954,0.11004,0.10712,-0.0675,0.0114,1.0000