Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-vr9-il-1000000-n5 Airfoil,vr9-il Reynolds number,1000000 Ncrit,5 Mach,0 Max Cl/Cd,55.9119 Max Cl/Cd alpha,4.75 Url,http://www.airfoiltools.com/polar/csv?polar=xf-vr9-il-1000000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.6222,0.08726,0.08567,0.0067,1.0000,0.0042 -8.250,-0.6334,0.08158,0.08003,0.0034,1.0000,0.0037 -8.000,-0.6405,0.07695,0.07542,-0.0003,1.0000,0.0037 -7.750,-0.6426,0.07159,0.07004,-0.0057,1.0000,0.0038 -7.500,-0.6434,0.06587,0.06427,-0.0096,1.0000,0.0036 -7.250,-0.6407,0.06037,0.05866,-0.0124,1.0000,0.0035 -7.000,-0.6340,0.05527,0.05344,-0.0141,1.0000,0.0034 -6.750,-0.6254,0.05008,0.04810,-0.0152,1.0000,0.0032 -6.500,-0.6145,0.04482,0.04263,-0.0156,1.0000,0.0030 -6.250,-0.6008,0.03992,0.03750,-0.0154,1.0000,0.0028 -6.000,-0.5858,0.03471,0.03200,-0.0146,1.0000,0.0026 -5.750,-0.5693,0.02940,0.02632,-0.0132,1.0000,0.0023 -5.500,-0.5519,0.02338,0.01981,-0.0111,1.0000,0.0021 -5.250,-0.5359,0.01532,0.01085,-0.0075,1.0000,0.0018 -5.000,-0.5098,0.01259,0.00774,-0.0069,0.9927,0.0017 -4.750,-0.4714,0.01128,0.00571,-0.0090,0.8063,0.0017 -4.500,-0.4495,0.01066,0.00455,-0.0077,0.7123,0.0018 -4.250,-0.4310,0.01172,0.00383,-0.0066,0.0502,0.0020 -4.000,-0.4049,0.01129,0.00331,-0.0062,0.0406,0.0028 -3.750,-0.3785,0.01101,0.00297,-0.0060,0.0376,0.0038 -3.500,-0.3516,0.01088,0.00281,-0.0059,0.0228,0.0065 -2.500,-0.2428,0.01070,0.00241,-0.0056,0.0222,0.0167 -2.000,-0.1907,0.00985,0.00136,-0.0051,0.0229,0.0203 -1.750,-0.1637,0.00971,0.00118,-0.0050,0.0229,0.0207 -1.250,-0.1093,0.00956,0.00094,-0.0049,0.0223,0.0212 -1.000,-0.0821,0.00949,0.00082,-0.0048,0.0224,0.0217 -0.750,-0.0548,0.00944,0.00073,-0.0047,0.0225,0.0222 -0.500,-0.0275,0.00942,0.00068,-0.0046,0.0227,0.0220 -0.250,-0.0001,0.00941,0.00065,-0.0046,0.0228,0.0218 0.000,0.0272,0.00941,0.00063,-0.0045,0.0229,0.0216 0.250,0.0545,0.00941,0.00064,-0.0045,0.0228,0.0214 0.500,0.0818,0.00944,0.00070,-0.0044,0.0222,0.0212 0.750,0.1090,0.00949,0.00078,-0.0043,0.0216,0.0209 1.000,0.1363,0.00953,0.00085,-0.0043,0.0212,0.0206 1.250,0.1635,0.00960,0.00093,-0.0042,0.0208,0.0204 1.500,0.1906,0.00970,0.00106,-0.0041,0.0202,0.0201 1.750,0.2175,0.00984,0.00125,-0.0040,0.0192,0.0198 2.000,0.2441,0.01009,0.00155,-0.0038,0.0172,0.0196 2.250,0.2712,0.01016,0.00166,-0.0038,0.0163,0.0195 2.500,0.2979,0.01038,0.00198,-0.0036,0.0151,0.0196 2.750,0.3245,0.01063,0.00228,-0.0034,0.0145,0.0198 3.000,0.3509,0.01094,0.00259,-0.0032,0.0143,0.0219 3.250,0.3771,0.01122,0.00299,-0.0029,0.0142,0.0363 3.500,0.4032,0.01156,0.00341,-0.0027,0.0143,0.0402 3.750,0.4295,0.01180,0.00369,-0.0025,0.0126,0.0441 4.000,0.4508,0.01017,0.00359,-0.0022,0.0107,0.6816 4.250,0.4741,0.00976,0.00369,-0.0012,0.0093,0.8126 4.500,0.5025,0.00925,0.00356,-0.0011,0.0032,0.9590 4.750,0.5457,0.00976,0.00422,-0.0047,0.0024,1.0000 5.000,0.5701,0.01038,0.00496,-0.0040,0.0023,1.0000 5.250,0.5941,0.01114,0.00586,-0.0033,0.0023,1.0000 5.500,0.6177,0.01213,0.00700,-0.0025,0.0023,1.0000 5.750,0.6408,0.01345,0.00851,-0.0015,0.0024,1.0000 6.000,0.6625,0.01584,0.01121,-0.0002,0.0025,1.0000 6.250,0.6772,0.02312,0.01935,0.0030,0.0028,1.0000 6.500,0.6918,0.02921,0.02599,0.0053,0.0030,1.0000 6.750,0.7046,0.03519,0.03240,0.0070,0.0033,1.0000 7.000,0.7155,0.04085,0.03840,0.0082,0.0035,1.0000 7.250,0.7252,0.04602,0.04383,0.0088,0.0035,1.0000 7.500,0.7325,0.05121,0.04922,0.0088,0.0034,1.0000 7.750,0.7382,0.05596,0.05413,0.0083,0.0031,1.0000 8.000,0.7393,0.06116,0.05947,0.0071,0.0031,1.0000 8.250,0.7365,0.06653,0.06495,0.0051,0.0029,1.0000 8.500,0.7234,0.07304,0.07154,0.0015,0.0033,1.0000 8.750,0.7110,0.07909,0.07759,-0.0053,0.0032,1.0000 9.000,0.7006,0.08576,0.08422,-0.0101,0.0039,1.0000