Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-vr9-il-200000-n5 Airfoil,vr9-il Reynolds number,200000 Ncrit,5 Mach,0 Max Cl/Cd,32.5093 Max Cl/Cd alpha,3.75 Url,http://www.airfoiltools.com/polar/csv?polar=xf-vr9-il-200000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.6356,0.08871,0.08528,0.0077,1.0000,0.0086 -8.250,-0.6378,0.08404,0.08065,0.0048,1.0000,0.0084 -8.000,-0.6412,0.07957,0.07623,0.0013,1.0000,0.0081 -7.750,-0.6448,0.07412,0.07078,-0.0038,1.0000,0.0081 -7.500,-0.6437,0.06874,0.06534,-0.0077,1.0000,0.0078 -7.250,-0.6404,0.06331,0.05981,-0.0106,1.0000,0.0077 -7.000,-0.6343,0.05811,0.05445,-0.0127,1.0000,0.0076 -6.750,-0.6254,0.05302,0.04917,-0.0140,1.0000,0.0074 -6.500,-0.6140,0.04803,0.04392,-0.0146,1.0000,0.0074 -6.250,-0.6000,0.04330,0.03888,-0.0147,1.0000,0.0078 -6.000,-0.5833,0.03892,0.03416,-0.0143,1.0000,0.0085 -5.750,-0.5635,0.03399,0.02868,-0.0130,1.0000,0.0096 -5.500,-0.5439,0.03001,0.02416,-0.0118,1.0000,0.0098 -5.250,-0.5232,0.02670,0.02024,-0.0106,1.0000,0.0099 -5.000,-0.5006,0.02389,0.01688,-0.0094,1.0000,0.0101 -4.750,-0.4779,0.02129,0.01394,-0.0085,1.0000,0.0104 -4.500,-0.4546,0.01948,0.01200,-0.0079,1.0000,0.0112 -4.250,-0.4302,0.01789,0.01018,-0.0071,1.0000,0.0126 -4.000,-0.4054,0.01674,0.00874,-0.0063,1.0000,0.0168 -3.750,-0.3821,0.01518,0.00714,-0.0053,1.0000,0.0193 -3.500,-0.3587,0.01401,0.00583,-0.0043,1.0000,0.0213 -3.250,-0.3364,0.01294,0.00477,-0.0035,1.0000,0.0255 -3.000,-0.3127,0.01223,0.00397,-0.0027,1.0000,0.0264 -2.750,-0.2884,0.01174,0.00336,-0.0020,1.0000,0.0281 -2.500,-0.2387,0.01136,0.00277,-0.0068,0.9296,0.0327 -2.250,-0.1992,0.01120,0.00228,-0.0089,0.8251,0.0400 -2.000,-0.1770,0.01148,0.00191,-0.0072,0.6841,0.0438 -1.750,-0.1532,0.01165,0.00158,-0.0063,0.5972,0.0455 -1.500,-0.1270,0.01161,0.00134,-0.0060,0.5668,0.0478 -1.250,-0.1011,0.01134,0.00112,-0.0057,0.5467,0.1010 -1.000,-0.0793,0.01020,0.00088,-0.0053,0.5297,0.3710 -0.750,-0.0517,0.01005,0.00078,-0.0053,0.5427,0.3903 -0.500,-0.0202,0.01109,0.00075,-0.0053,0.5263,0.1415 -0.250,0.0087,0.01130,0.00074,-0.0053,0.5410,0.0507 0.000,0.0368,0.01120,0.00072,-0.0054,0.5587,0.0466 0.250,0.0647,0.01110,0.00073,-0.0054,0.5734,0.0456 0.500,0.0922,0.01105,0.00076,-0.0054,0.5758,0.0450 0.750,0.1196,0.01103,0.00081,-0.0053,0.5727,0.0446 1.000,0.1464,0.01106,0.00086,-0.0051,0.5581,0.0443 1.250,0.1729,0.01114,0.00094,-0.0048,0.5327,0.0448 1.500,0.1986,0.01131,0.00105,-0.0044,0.4862,0.0458 1.750,0.2193,0.01179,0.00121,-0.0037,0.2934,0.2074 2.000,0.2292,0.01134,0.00163,-0.0014,0.0457,0.7323 2.250,0.2550,0.01115,0.00194,-0.0005,0.0396,0.8650 2.500,0.3123,0.01132,0.00241,-0.0068,0.0322,1.0000 2.750,0.3376,0.01158,0.00276,-0.0063,0.0288,1.0000 3.000,0.3627,0.01191,0.00323,-0.0057,0.0273,1.0000 3.250,0.3877,0.01231,0.00370,-0.0052,0.0267,1.0000 3.500,0.4124,0.01280,0.00431,-0.0046,0.0265,1.0000 3.750,0.4366,0.01343,0.00506,-0.0039,0.0264,1.0000 4.000,0.4603,0.01419,0.00588,-0.0033,0.0248,1.0000 4.250,0.4826,0.01540,0.00710,-0.0024,0.0220,1.0000 4.500,0.5045,0.01703,0.00871,-0.0016,0.0172,1.0000 4.750,0.5289,0.01845,0.01052,-0.0007,0.0142,1.0000 5.000,0.5533,0.02014,0.01246,0.0002,0.0125,1.0000 5.250,0.5763,0.02220,0.01455,0.0008,0.0115,1.0000 5.500,0.6002,0.02445,0.01742,0.0021,0.0107,1.0000 5.750,0.6236,0.02686,0.02046,0.0034,0.0083,1.0000 6.000,0.6442,0.03004,0.02411,0.0046,0.0077,1.0000 6.250,0.6626,0.03376,0.02829,0.0058,0.0074,1.0000 6.500,0.6787,0.03806,0.03305,0.0070,0.0074,1.0000 6.750,0.6923,0.04278,0.03817,0.0078,0.0075,1.0000 7.000,0.7030,0.04785,0.04360,0.0082,0.0077,1.0000 7.250,0.7108,0.05308,0.04912,0.0082,0.0079,1.0000 7.500,0.7152,0.05839,0.05467,0.0074,0.0081,1.0000 7.750,0.7165,0.06369,0.06015,0.0060,0.0084,1.0000 8.000,0.7145,0.06905,0.06563,0.0037,0.0086,1.0000 8.250,0.7086,0.07449,0.07115,0.0004,0.0088,1.0000 8.500,0.6992,0.08061,0.07725,-0.0055,0.0089,1.0000 8.750,0.6941,0.08626,0.08285,-0.0099,0.0090,1.0000