Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-vr9-il-500000 Airfoil,vr9-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,39.7981 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-vr9-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.6348,0.08719,0.08499,0.0065,1.0000,0.0105 -8.250,-0.6374,0.08266,0.08049,0.0036,1.0000,0.0106 -8.000,-0.6442,0.07791,0.07578,-0.0003,1.0000,0.0109 -7.750,-0.6475,0.07254,0.07039,-0.0054,1.0000,0.0108 -7.500,-0.6462,0.06721,0.06500,-0.0092,1.0000,0.0110 -7.250,-0.6419,0.06204,0.05973,-0.0118,1.0000,0.0114 -7.000,-0.6339,0.05705,0.05459,-0.0137,1.0000,0.0120 -6.750,-0.6194,0.05261,0.04996,-0.0145,1.0000,0.0130 -6.500,-0.6020,0.04862,0.04573,-0.0145,1.0000,0.0135 -6.250,-0.5877,0.04445,0.04130,-0.0142,1.0000,0.0136 -6.000,-0.5725,0.04036,0.03693,-0.0137,1.0000,0.0137 -5.750,-0.5561,0.03653,0.03279,-0.0129,1.0000,0.0137 -5.500,-0.5380,0.03333,0.02924,-0.0119,1.0000,0.0138 -5.250,-0.5188,0.03031,0.02587,-0.0109,1.0000,0.0138 -5.000,-0.5050,0.02374,0.01881,-0.0097,1.0000,0.0146 -4.750,-0.4837,0.02099,0.01577,-0.0088,1.0000,0.0152 -4.500,-0.4607,0.01891,0.01348,-0.0079,1.0000,0.0157 -4.250,-0.4371,0.01708,0.01145,-0.0070,1.0000,0.0167 -4.000,-0.4127,0.01539,0.00955,-0.0060,1.0000,0.0179 -3.750,-0.3880,0.01378,0.00774,-0.0049,1.0000,0.0194 -3.500,-0.3632,0.01289,0.00670,-0.0039,1.0000,0.0218 -3.250,-0.3412,0.01108,0.00479,-0.0025,1.0000,0.0231 -3.000,-0.3186,0.01005,0.00366,-0.0013,1.0000,0.0241 -2.750,-0.2952,0.00939,0.00295,-0.0004,1.0000,0.0263 -2.500,-0.2596,0.00890,0.00242,-0.0021,0.9903,0.0296 -2.250,-0.2005,0.00847,0.00176,-0.0088,0.8946,0.0325 -2.000,-0.1796,0.00871,0.00149,-0.0068,0.7656,0.0353 -1.750,-0.1551,0.00881,0.00126,-0.0060,0.7017,0.0383 -1.500,-0.1296,0.00890,0.00107,-0.0055,0.6473,0.0399 -1.250,-0.1033,0.00893,0.00091,-0.0052,0.6097,0.0405 -1.000,-0.0765,0.00895,0.00079,-0.0050,0.5813,0.0406 -0.750,-0.0495,0.00896,0.00071,-0.0048,0.5564,0.0406 -0.500,-0.0226,0.00900,0.00063,-0.0046,0.5297,0.0407 -0.250,-0.0017,0.01038,0.00072,-0.0041,0.1454,0.0408 0.000,0.0246,0.01067,0.00073,-0.0040,0.0521,0.0415 0.250,0.0518,0.01069,0.00073,-0.0039,0.0492,0.0430 0.500,0.0790,0.01070,0.00075,-0.0038,0.0472,0.0469 0.750,0.1062,0.01068,0.00081,-0.0037,0.0463,0.0606 1.000,0.1246,0.00886,0.00079,-0.0028,0.0460,0.6320 1.250,0.1492,0.00863,0.00088,-0.0021,0.0457,0.7133 1.500,0.1702,0.00824,0.00101,-0.0004,0.0454,0.8392 1.750,0.2151,0.00814,0.00124,-0.0037,0.0425,0.9707 2.000,0.2655,0.00828,0.00147,-0.0088,0.0399,1.0000 2.250,0.2907,0.00843,0.00166,-0.0082,0.0358,1.0000 2.500,0.3157,0.00866,0.00191,-0.0076,0.0313,1.0000 2.750,0.3406,0.00896,0.00225,-0.0069,0.0299,1.0000 3.000,0.3653,0.00936,0.00273,-0.0062,0.0294,1.0000 3.250,0.3898,0.00981,0.00325,-0.0056,0.0276,1.0000 3.500,0.4139,0.01040,0.00390,-0.0048,0.0266,1.0000 3.750,0.4372,0.01125,0.00481,-0.0038,0.0249,1.0000 4.000,0.4591,0.01282,0.00649,-0.0025,0.0221,1.0000 4.250,0.4834,0.01412,0.00791,-0.0015,0.0204,1.0000 4.500,0.5079,0.01561,0.00954,-0.0006,0.0184,1.0000 4.750,0.5320,0.01730,0.01137,0.0002,0.0172,1.0000 5.000,0.5531,0.02115,0.01549,0.0012,0.0156,1.0000 5.250,0.5740,0.02444,0.01926,0.0025,0.0152,1.0000 5.500,0.5949,0.02745,0.02264,0.0037,0.0152,1.0000 5.750,0.6140,0.03095,0.02654,0.0050,0.0151,1.0000 6.000,0.6316,0.03453,0.03049,0.0062,0.0151,1.0000 6.250,0.6483,0.03808,0.03436,0.0073,0.0150,1.0000 6.500,0.6645,0.04153,0.03812,0.0082,0.0148,1.0000 6.750,0.6853,0.04451,0.04141,0.0093,0.0135,1.0000 7.000,0.6981,0.04873,0.04587,0.0096,0.0125,1.0000 7.250,0.7072,0.05323,0.05058,0.0095,0.0120,1.0000 7.500,0.7130,0.05791,0.05543,0.0088,0.0116,1.0000 7.750,0.7153,0.06282,0.06048,0.0076,0.0114,1.0000 8.000,0.7140,0.06790,0.06567,0.0055,0.0112,1.0000 8.250,0.7082,0.07336,0.07121,0.0023,0.0112,1.0000 8.500,0.6952,0.07959,0.07744,-0.0040,0.0114,1.0000 8.750,0.6899,0.08500,0.08282,-0.0082,0.0115,1.0000