Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-vr9-il-50000 Airfoil,vr9-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,24.3179 Max Cl/Cd alpha,3 Url,http://airfoiltools.com/polar/csv?polar=xf-vr9-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.500,-0.6638,0.12250,0.11579,0.0246,1.0000,0.2142 -9.250,-0.6424,0.11658,0.10985,0.0267,1.0000,0.2320 -9.000,-0.6580,0.11517,0.10855,0.0242,1.0000,0.2416 -8.750,-0.6348,0.10937,0.10271,0.0264,1.0000,0.2594 -8.500,-0.6283,0.10569,0.09907,0.0267,1.0000,0.2758 -8.250,-0.6294,0.10271,0.09615,0.0267,1.0000,0.2939 -8.000,-0.6406,0.10058,0.09406,0.0260,1.0000,0.3098 -7.750,-0.6212,0.09602,0.08949,0.0282,1.0000,0.3356 -7.500,-0.6093,0.09217,0.08566,0.0299,1.0000,0.3615 -7.250,-0.6023,0.08886,0.08239,0.0315,1.0000,0.3893 -7.000,-0.6029,0.08622,0.07983,0.0334,1.0000,0.4187 -6.750,-0.5863,0.08212,0.07574,0.0353,1.0000,0.4484 -6.500,-0.5636,0.07812,0.07172,0.0382,1.0000,0.4919 -5.250,-0.5509,0.04272,0.03403,-0.0150,1.0000,0.1308 -5.000,-0.5255,0.03853,0.02922,-0.0146,1.0000,0.1159 -4.750,-0.5010,0.03505,0.02521,-0.0139,1.0000,0.1120 -4.500,-0.4755,0.03213,0.02180,-0.0131,1.0000,0.1125 -4.250,-0.4474,0.02934,0.01841,-0.0121,1.0000,0.1092 -4.000,-0.4187,0.02695,0.01556,-0.0110,1.0000,0.1082 -3.750,-0.3902,0.02473,0.01318,-0.0100,1.0000,0.1108 -3.500,-0.3631,0.02290,0.01129,-0.0090,1.0000,0.1233 -3.250,-0.3355,0.02134,0.00951,-0.0078,1.0000,0.1337 -3.000,-0.3106,0.01981,0.00801,-0.0067,1.0000,0.1493 -2.750,-0.1933,0.01555,0.00654,-0.0148,1.0000,1.0000 -2.500,-0.1772,0.01512,0.00578,-0.0138,1.0000,1.0000 -2.250,-0.1604,0.01478,0.00515,-0.0127,1.0000,1.0000 -2.000,-0.1426,0.01452,0.00457,-0.0116,1.0000,1.0000 -1.750,-0.1241,0.01432,0.00415,-0.0105,1.0000,1.0000 -1.500,-0.1050,0.01417,0.00380,-0.0094,1.0000,1.0000 -1.250,-0.0853,0.01406,0.00352,-0.0083,1.0000,1.0000 -1.000,-0.0654,0.01398,0.00331,-0.0072,1.0000,1.0000 -0.750,-0.0454,0.01393,0.00315,-0.0061,1.0000,1.0000 -0.500,-0.0253,0.01390,0.00299,-0.0050,1.0000,1.0000 -0.250,-0.0052,0.01389,0.00293,-0.0039,1.0000,1.0000 0.000,0.0149,0.01390,0.00291,-0.0027,1.0000,1.0000 0.250,0.0349,0.01394,0.00295,-0.0016,1.0000,1.0000 0.500,0.0546,0.01400,0.00303,-0.0005,1.0000,1.0000 0.750,0.0742,0.01409,0.00318,0.0005,1.0000,1.0000 1.000,0.0932,0.01422,0.00339,0.0016,1.0000,1.0000 1.250,0.1116,0.01440,0.00364,0.0027,1.0000,1.0000 1.500,0.1292,0.01463,0.00397,0.0039,1.0000,1.0000 1.750,0.1460,0.01492,0.00438,0.0049,1.0000,1.0000 2.000,0.1622,0.01529,0.00485,0.0059,1.0000,1.0000 2.250,0.1780,0.01572,0.00542,0.0068,1.0000,1.0000 2.500,0.1935,0.01621,0.00614,0.0075,1.0000,1.0000 2.750,0.2089,0.01679,0.00688,0.0081,1.0000,1.0000 3.000,0.3886,0.01598,0.00772,-0.0145,0.8415,1.0000 3.250,0.3927,0.01672,0.00697,-0.0021,0.4100,1.0000 3.500,0.4053,0.02020,0.00850,0.0000,0.1604,1.0000 3.750,0.4298,0.02184,0.01010,0.0011,0.1365,1.0000 4.000,0.4547,0.02350,0.01170,0.0021,0.1187,1.0000 4.250,0.4828,0.02529,0.01365,0.0034,0.1120,1.0000 4.500,0.5115,0.02763,0.01606,0.0044,0.1084,1.0000 4.750,0.5400,0.03037,0.01907,0.0054,0.1076,1.0000 5.000,0.5664,0.03300,0.02235,0.0064,0.1045,1.0000 5.250,0.5915,0.03598,0.02590,0.0073,0.1033,1.0000 5.500,0.6156,0.04014,0.03026,0.0080,0.1069,1.0000 5.750,0.6391,0.04395,0.03509,0.0089,0.1187,1.0000 6.000,0.6610,0.04904,0.04119,0.0086,0.1408,1.0000 6.250,0.6858,0.05667,0.04942,0.0065,0.1881,1.0000 7.000,0.6292,0.08425,0.07775,-0.0404,0.4459,1.0000 7.250,0.6371,0.08765,0.08113,-0.0390,0.4214,1.0000 7.500,0.6348,0.09044,0.08384,-0.0380,0.3993,1.0000 7.750,0.6536,0.09501,0.08843,-0.0369,0.3798,1.0000 8.000,0.6475,0.09761,0.09102,-0.0363,0.3586,1.0000 8.250,0.6753,0.10323,0.09670,-0.0345,0.3378,1.0000