Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-mh20-il-1000000 Airfoil,mh20-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,105.526 Max Cl/Cd alpha,4.25 Url,http://airfoiltools.com/polar/csv?polar=xf-mh20-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -3.750,-0.3078,0.01153,0.00573,-0.0089,0.7167,0.0062 -3.500,-0.2831,0.01040,0.00441,-0.0079,0.7113,0.0057 -3.250,-0.2574,0.00963,0.00348,-0.0072,0.7055,0.0054 -2.750,-0.2037,0.00879,0.00239,-0.0063,0.6950,0.0053 -2.500,-0.1763,0.00855,0.00203,-0.0060,0.6898,0.0055 -2.250,-0.1487,0.00837,0.00176,-0.0057,0.6850,0.0067 -2.000,-0.1231,0.00778,0.00147,-0.0053,0.6800,0.0829 -1.750,-0.0974,0.00735,0.00134,-0.0051,0.6753,0.1666 -1.250,-0.0475,0.00634,0.00114,-0.0043,0.6659,0.4053 -1.000,-0.0247,0.00574,0.00105,-0.0035,0.6613,0.5721 -0.750,-0.0014,0.00530,0.00100,-0.0026,0.6568,0.6903 -0.500,0.0190,0.00478,0.00096,-0.0008,0.6520,0.8316 -0.250,0.0707,0.00463,0.00107,-0.0057,0.6469,0.9449 0.250,0.1483,0.00484,0.00118,-0.0102,0.6362,0.9780 0.500,0.1871,0.00492,0.00122,-0.0125,0.6308,0.9839 0.750,0.2281,0.00496,0.00123,-0.0154,0.6245,0.9885 1.000,0.2657,0.00505,0.00126,-0.0176,0.6185,0.9928 1.250,0.3061,0.00506,0.00125,-0.0203,0.6112,0.9956 1.500,0.3472,0.00506,0.00122,-0.0233,0.6042,0.9988 1.750,0.3804,0.00506,0.00121,-0.0245,0.5960,1.0000 2.000,0.4065,0.00508,0.00120,-0.0242,0.5876,1.0000 2.250,0.4326,0.00511,0.00120,-0.0239,0.5777,1.0000 2.500,0.4588,0.00514,0.00121,-0.0236,0.5665,1.0000 2.750,0.4851,0.00519,0.00122,-0.0233,0.5529,1.0000 3.000,0.5113,0.00524,0.00127,-0.0230,0.5357,1.0000 3.250,0.5376,0.00534,0.00131,-0.0227,0.5143,1.0000 3.500,0.5637,0.00548,0.00137,-0.0225,0.4891,1.0000 3.750,0.5898,0.00566,0.00146,-0.0222,0.4614,1.0000 4.000,0.6158,0.00586,0.00159,-0.0220,0.4344,1.0000 4.250,0.6416,0.00608,0.00173,-0.0218,0.4070,1.0000 4.500,0.6673,0.00633,0.00188,-0.0215,0.3777,1.0000 4.750,0.6922,0.00674,0.00209,-0.0213,0.3265,1.0000 5.000,0.7163,0.00732,0.00236,-0.0210,0.2597,1.0000 5.250,0.7400,0.00793,0.00267,-0.0207,0.1964,1.0000 5.500,0.7640,0.00841,0.00298,-0.0203,0.1560,1.0000 5.750,0.7868,0.00909,0.00343,-0.0198,0.1023,1.0000 6.000,0.8081,0.00997,0.00398,-0.0191,0.0429,1.0000 6.250,0.8285,0.01099,0.00478,-0.0182,0.0039,1.0000 6.500,0.8521,0.01144,0.00532,-0.0174,0.0032,1.0000 6.750,0.8750,0.01195,0.00593,-0.0166,0.0030,1.0000 7.000,0.8970,0.01258,0.00666,-0.0157,0.0029,1.0000 7.250,0.9179,0.01331,0.00752,-0.0146,0.0029,1.0000 7.500,0.9368,0.01427,0.00860,-0.0132,0.0029,1.0000 7.750,0.9532,0.01544,0.00993,-0.0114,0.0029,1.0000 8.000,0.9680,0.01675,0.01138,-0.0095,0.0030,1.0000 8.250,0.9804,0.01839,0.01318,-0.0071,0.0032,1.0000 8.500,0.9926,0.02023,0.01517,-0.0048,0.0033,1.0000 8.750,1.0018,0.02314,0.01835,-0.0021,0.0036,1.0000 9.000,1.0194,0.02448,0.01974,-0.0006,0.0044,1.0000 12.000,0.9336,0.06658,0.06440,0.0172,0.0064,1.0000 12.250,0.9183,0.07196,0.06990,0.0143,0.0064,1.0000 12.500,0.8942,0.07973,0.07781,0.0096,0.0066,1.0000 12.750,0.8741,0.08762,0.08581,0.0043,0.0067,1.0000 13.000,0.8435,0.09927,0.09757,-0.0035,0.0073,1.0000