Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-vr8b-il-200000 Airfoil,vr8b-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,46.9875 Max Cl/Cd alpha,3.75 Url,http://airfoiltools.com/polar/csv?polar=xf-vr8b-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.750,-0.6773,0.12276,0.11957,0.0438,1.0000,0.0277 -9.500,-0.6743,0.11847,0.11531,0.0415,1.0000,0.0288 -7.500,-0.6644,0.07499,0.07189,0.0037,1.0000,0.0343 -7.250,-0.6550,0.07144,0.06831,0.0023,1.0000,0.0360 -7.000,-0.6444,0.06666,0.06341,-0.0012,1.0000,0.0384 -6.750,-0.6253,0.06263,0.05873,-0.0069,1.0000,0.0428 -6.500,-0.5711,0.04231,0.03883,-0.0122,1.0000,0.0456 -6.250,-0.5566,0.03872,0.03519,-0.0129,1.0000,0.0497 -5.750,-0.5609,0.04369,0.03928,-0.0126,1.0000,0.0592 -5.500,-0.5365,0.04075,0.03575,-0.0139,1.0000,0.0699 -5.250,-0.5141,0.03736,0.03250,-0.0147,1.0000,0.0747 -5.000,-0.4878,0.03422,0.02889,-0.0157,1.0000,0.0852 -4.750,-0.4606,0.03184,0.02638,-0.0163,1.0000,0.0931 -4.500,-0.4337,0.02907,0.02339,-0.0172,1.0000,0.1059 -4.250,-0.3913,0.02258,0.01567,-0.0154,1.0000,0.0501 -4.000,-0.3581,0.02020,0.01268,-0.0149,1.0000,0.0439 -3.750,-0.3274,0.01856,0.01087,-0.0151,1.0000,0.0425 -3.500,-0.2970,0.01718,0.00934,-0.0154,1.0000,0.0430 -3.250,-0.2682,0.01505,0.00720,-0.0158,1.0000,0.0453 -3.000,-0.2385,0.01391,0.00606,-0.0163,1.0000,0.0458 -2.750,-0.2086,0.01300,0.00517,-0.0170,1.0000,0.0472 -2.500,-0.1785,0.01233,0.00451,-0.0179,1.0000,0.0495 -2.250,-0.1444,0.01189,0.00404,-0.0197,0.9908,0.0539 -2.000,-0.1041,0.01150,0.00357,-0.0224,0.9727,0.0592 -1.750,-0.0783,0.01124,0.00342,-0.0217,0.9448,0.0918 -1.500,-0.0613,0.00896,0.00333,-0.0203,0.9183,0.6387 -1.250,-0.0517,0.00856,0.00333,-0.0149,0.8845,0.7575 -1.000,-0.0421,0.00839,0.00322,-0.0093,0.8496,0.8232 -0.750,-0.0279,0.00830,0.00311,-0.0051,0.8247,0.8829 -0.500,-0.0100,0.00824,0.00296,-0.0018,0.8053,0.9561 -0.250,0.0281,0.00813,0.00269,-0.0037,0.7856,1.0000 0.000,0.0553,0.00820,0.00258,-0.0036,0.7681,1.0000 0.250,0.0810,0.00829,0.00239,-0.0029,0.7350,1.0000 0.500,0.1080,0.00840,0.00223,-0.0026,0.6992,1.0000 0.750,0.1366,0.00849,0.00216,-0.0028,0.6794,1.0000 1.000,0.1655,0.00859,0.00211,-0.0030,0.6623,1.0000 1.250,0.1946,0.00868,0.00210,-0.0034,0.6475,1.0000 1.500,0.2239,0.00878,0.00212,-0.0037,0.6335,1.0000 1.750,0.2531,0.00889,0.00215,-0.0041,0.6191,1.0000 2.000,0.2824,0.00900,0.00219,-0.0044,0.6023,1.0000 2.250,0.3118,0.00911,0.00228,-0.0048,0.5838,1.0000 2.500,0.3412,0.00922,0.00236,-0.0052,0.5655,1.0000 2.750,0.3707,0.00935,0.00247,-0.0056,0.5473,1.0000 3.000,0.4002,0.00948,0.00260,-0.0060,0.5273,1.0000 3.250,0.4296,0.00964,0.00276,-0.0064,0.5002,1.0000 3.500,0.4590,0.00986,0.00291,-0.0069,0.4572,1.0000 3.750,0.4882,0.01039,0.00308,-0.0075,0.3549,1.0000 4.000,0.5170,0.01200,0.00372,-0.0092,0.1515,1.0000 4.250,0.5458,0.01319,0.00446,-0.0103,0.0584,1.0000 4.500,0.5749,0.01376,0.00506,-0.0107,0.0519,1.0000 4.750,0.6038,0.01432,0.00573,-0.0112,0.0498,1.0000 5.000,0.6324,0.01498,0.00649,-0.0116,0.0481,1.0000 5.250,0.6602,0.01581,0.00738,-0.0120,0.0456,1.0000 5.500,0.6872,0.01689,0.00853,-0.0123,0.0444,1.0000 5.750,0.7131,0.01825,0.00993,-0.0123,0.0436,1.0000 6.000,0.7390,0.01973,0.01146,-0.0121,0.0424,1.0000 6.250,0.7661,0.02081,0.01267,-0.0119,0.0407,1.0000 6.500,0.7927,0.02244,0.01445,-0.0116,0.0396,1.0000 6.750,0.8190,0.02383,0.01597,-0.0115,0.0365,1.0000 7.000,0.8454,0.02627,0.01868,-0.0110,0.0363,1.0000 7.250,0.8710,0.03055,0.02360,-0.0100,0.0393,1.0000 13.250,0.6429,0.15188,0.14872,-0.0436,0.0483,1.0000 13.500,0.6449,0.15441,0.15126,-0.0441,0.0458,1.0000 13.750,0.8571,0.17806,0.17471,-0.0721,0.0332,1.0000 14.000,0.8558,0.18366,0.18027,-0.0783,0.0304,1.0000 14.250,0.6495,0.16428,0.16113,-0.0461,0.0421,1.0000