Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-vr9-il-100000 Airfoil,vr9-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,31.1993 Max Cl/Cd alpha,2.5 Url,http://www.airfoiltools.com/polar/csv?polar=xf-vr9-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.6493,0.09257,0.08794,0.0047,1.0000,0.0905 -8.000,-0.6627,0.08807,0.08347,-0.0031,1.0000,0.0916 -7.750,-0.6745,0.08444,0.07965,-0.0096,1.0000,0.0923 -7.500,-0.6484,0.07941,0.07486,-0.0020,1.0000,0.1004 -7.250,-0.6584,0.07506,0.07026,-0.0105,1.0000,0.1054 -7.000,-0.6462,0.06976,0.06509,-0.0088,1.0000,0.1094 -6.750,-0.6486,0.06751,0.06227,-0.0140,1.0000,0.1195 -6.500,-0.6298,0.06149,0.05667,-0.0113,1.0000,0.1243 -6.250,-0.6205,0.05745,0.05247,-0.0126,1.0000,0.1363 -6.000,-0.6082,0.05389,0.04876,-0.0128,1.0000,0.1504 -5.750,-0.5971,0.05081,0.04546,-0.0133,1.0000,0.1749 -5.500,-0.5836,0.04780,0.04248,-0.0122,1.0000,0.2025 -4.500,-0.4691,0.02828,0.01999,-0.0119,1.0000,0.0733 -4.250,-0.4407,0.02547,0.01650,-0.0103,1.0000,0.0631 -4.000,-0.4143,0.02281,0.01352,-0.0092,1.0000,0.0604 -3.750,-0.3876,0.02090,0.01133,-0.0081,1.0000,0.0618 -3.500,-0.3612,0.01940,0.00960,-0.0071,1.0000,0.0662 -3.250,-0.3365,0.01756,0.00775,-0.0061,1.0000,0.0686 -3.000,-0.3131,0.01630,0.00655,-0.0049,1.0000,0.0729 -2.750,-0.2904,0.01530,0.00555,-0.0038,1.0000,0.0837 -2.500,-0.2670,0.01444,0.00460,-0.0027,1.0000,0.0936 -2.250,-0.2466,0.01267,0.00361,-0.0015,1.0000,0.2279 -2.000,-0.2398,0.01032,0.00372,0.0046,1.0000,0.8154 -1.750,-0.1523,0.01034,0.00342,-0.0051,1.0000,0.9778 -1.500,-0.1013,0.01021,0.00300,-0.0103,1.0000,1.0000 -1.250,-0.0828,0.01008,0.00274,-0.0090,1.0000,1.0000 -1.000,-0.0636,0.00999,0.00254,-0.0077,1.0000,1.0000 -0.750,-0.0441,0.00993,0.00241,-0.0064,1.0000,1.0000 -0.500,-0.0247,0.00990,0.00229,-0.0051,1.0000,1.0000 -0.250,-0.0054,0.00990,0.00224,-0.0038,1.0000,1.0000 0.000,0.0139,0.00992,0.00225,-0.0024,1.0000,1.0000 0.250,0.0332,0.00996,0.00230,-0.0011,1.0000,1.0000 0.500,0.0521,0.01004,0.00240,0.0002,1.0000,1.0000 0.750,0.0703,0.01017,0.00256,0.0015,1.0000,1.0000 1.000,0.0872,0.01035,0.00281,0.0029,1.0000,1.0000 1.250,0.1039,0.01060,0.00311,0.0041,0.9995,1.0000 1.500,0.1792,0.01067,0.00340,-0.0057,0.9698,1.0000 1.750,0.2423,0.01057,0.00352,-0.0123,0.9306,1.0000 2.000,0.2867,0.01055,0.00374,-0.0150,0.8895,1.0000 2.250,0.3187,0.01062,0.00392,-0.0148,0.8400,1.0000 2.500,0.3382,0.01084,0.00391,-0.0110,0.7379,1.0000 2.750,0.3520,0.01159,0.00388,-0.0064,0.5276,1.0000 3.000,0.3631,0.01456,0.00464,-0.0039,0.1007,1.0000 3.250,0.3860,0.01561,0.00566,-0.0029,0.0800,1.0000 3.500,0.4095,0.01650,0.00668,-0.0018,0.0735,1.0000 3.750,0.4322,0.01771,0.00787,-0.0006,0.0695,1.0000 4.000,0.4557,0.01961,0.00965,0.0006,0.0672,1.0000 4.250,0.4819,0.02080,0.01107,0.0015,0.0613,1.0000 4.500,0.5087,0.02286,0.01334,0.0026,0.0605,1.0000 4.750,0.5357,0.02548,0.01633,0.0037,0.0626,1.0000 5.000,0.5613,0.02867,0.01995,0.0048,0.0653,1.0000 5.250,0.5854,0.03154,0.02330,0.0060,0.0650,1.0000 5.500,0.6101,0.03701,0.02920,0.0071,0.0797,1.0000 6.750,0.6974,0.06225,0.05749,0.0043,0.1531,1.0000 7.000,0.7027,0.06647,0.06180,0.0033,0.1412,1.0000 7.750,0.6337,0.07224,0.06802,-0.0018,0.1315,1.0000 8.000,0.6117,0.07739,0.07309,-0.0067,0.1287,1.0000 8.250,0.6427,0.08173,0.07746,-0.0005,0.1199,1.0000 8.500,0.6162,0.08683,0.08248,-0.0069,0.1192,1.0000 8.750,0.5965,0.09153,0.08710,-0.0118,0.1160,1.0000