Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-vr9-il-100000-n5 Airfoil,vr9-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,27.4322 Max Cl/Cd alpha,2.25 Url,http://airfoiltools.com/polar/csv?polar=xf-vr9-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.6361,0.10248,0.09766,0.0127,1.0000,0.0409 -8.750,-0.6352,0.09840,0.09363,0.0104,1.0000,0.0423 -8.500,-0.6360,0.09413,0.08941,0.0076,1.0000,0.0438 -6.750,-0.5805,0.04728,0.04253,-0.0147,1.0000,0.0327 -6.500,-0.5768,0.04096,0.03598,-0.0156,1.0000,0.0290 -6.250,-0.5989,0.04815,0.04234,-0.0152,1.0000,0.0252 -6.000,-0.5809,0.04307,0.03662,-0.0145,1.0000,0.0208 -5.750,-0.5646,0.03914,0.03243,-0.0141,1.0000,0.0199 -5.500,-0.5456,0.03540,0.02815,-0.0134,1.0000,0.0194 -5.250,-0.5247,0.03198,0.02424,-0.0124,1.0000,0.0191 -5.000,-0.5021,0.02893,0.02065,-0.0114,1.0000,0.0198 -4.750,-0.4797,0.02625,0.01749,-0.0106,1.0000,0.0229 -4.500,-0.4552,0.02402,0.01491,-0.0097,1.0000,0.0249 -4.250,-0.4298,0.02172,0.01227,-0.0086,1.0000,0.0257 -4.000,-0.4049,0.01975,0.01010,-0.0075,1.0000,0.0270 -3.750,-0.3808,0.01880,0.00911,-0.0069,1.0000,0.0332 -3.500,-0.3568,0.01760,0.00778,-0.0059,1.0000,0.0356 -3.250,-0.3348,0.01628,0.00640,-0.0048,1.0000,0.0379 -3.000,-0.3114,0.01545,0.00544,-0.0039,1.0000,0.0412 -2.750,-0.2873,0.01484,0.00458,-0.0031,1.0000,0.0466 -2.500,-0.2633,0.01423,0.00397,-0.0024,1.0000,0.0581 -2.250,-0.2392,0.01366,0.00341,-0.0016,1.0000,0.0789 -2.000,-0.2213,0.01163,0.00292,-0.0008,1.0000,0.4264 -1.750,-0.2034,0.01070,0.00283,0.0015,1.0000,0.6517 -1.500,-0.1816,0.01035,0.00262,0.0033,1.0000,0.7338 -1.250,-0.1573,0.01014,0.00249,0.0045,1.0000,0.7945 -1.000,-0.1184,0.00996,0.00243,0.0030,1.0000,0.8963 -0.750,-0.0734,0.00990,0.00229,-0.0005,1.0000,0.9519 -0.500,-0.0363,0.00986,0.00215,-0.0028,1.0000,0.9823 -0.250,0.0026,0.00985,0.00207,-0.0055,0.9912,1.0000 0.000,0.0420,0.00988,0.00205,-0.0082,0.9603,1.0000 0.250,0.0807,0.00991,0.00205,-0.0106,0.9281,1.0000 0.500,0.1167,0.00995,0.00209,-0.0124,0.8976,1.0000 0.750,0.1500,0.01000,0.00213,-0.0135,0.8680,1.0000 1.000,0.1800,0.01008,0.00220,-0.0139,0.8393,1.0000 1.250,0.2075,0.01018,0.00232,-0.0137,0.8128,1.0000 1.500,0.2338,0.01030,0.00250,-0.0131,0.7877,1.0000 1.750,0.2590,0.01044,0.00268,-0.0123,0.7586,1.0000 2.000,0.2819,0.01069,0.00281,-0.0108,0.7023,1.0000 2.250,0.3034,0.01106,0.00295,-0.0089,0.6206,1.0000 2.500,0.3223,0.01187,0.00303,-0.0068,0.4313,1.0000 2.750,0.3377,0.01420,0.00358,-0.0057,0.0650,1.0000 3.000,0.3617,0.01488,0.00426,-0.0050,0.0478,1.0000 3.250,0.3865,0.01541,0.00496,-0.0043,0.0431,1.0000 3.500,0.4108,0.01604,0.00576,-0.0036,0.0404,1.0000 3.750,0.4346,0.01681,0.00670,-0.0028,0.0386,1.0000 4.000,0.4575,0.01780,0.00783,-0.0019,0.0373,1.0000 4.250,0.4793,0.01935,0.00943,-0.0008,0.0354,1.0000 4.500,0.5043,0.02019,0.01046,0.0000,0.0298,1.0000 4.750,0.5283,0.02186,0.01233,0.0009,0.0277,1.0000 5.000,0.5525,0.02393,0.01459,0.0018,0.0249,1.0000 5.250,0.5752,0.02639,0.01723,0.0024,0.0211,1.0000 5.500,0.5991,0.02908,0.02046,0.0036,0.0205,1.0000 5.750,0.6212,0.03222,0.02416,0.0048,0.0202,1.0000 6.000,0.6413,0.03570,0.02817,0.0059,0.0204,1.0000 6.250,0.6589,0.03955,0.03245,0.0068,0.0208,1.0000 6.500,0.6765,0.04414,0.03776,0.0082,0.0238,1.0000 6.750,0.6891,0.04875,0.04276,0.0087,0.0251,1.0000 7.000,0.6994,0.05325,0.04760,0.0088,0.0254,1.0000 7.250,0.7069,0.05791,0.05256,0.0086,0.0254,1.0000 7.500,0.7116,0.06263,0.05751,0.0079,0.0255,1.0000 7.750,0.7144,0.06714,0.06216,0.0070,0.0260,1.0000 8.000,0.7159,0.07155,0.06665,0.0061,0.0263,1.0000 8.250,0.7163,0.07599,0.07114,0.0051,0.0265,1.0000 8.500,0.7132,0.08056,0.07577,0.0036,0.0266,1.0000