Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-eh1070-il-500000 Airfoil,eh1070-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,67.0856 Max Cl/Cd alpha,3.75 Url,http://airfoiltools.com/polar/csv?polar=xf-eh1070-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.5147,0.08129,0.07931,0.0054,1.0000,0.0139 -8.250,-0.5175,0.07628,0.07432,0.0031,1.0000,0.0139 -8.000,-0.5225,0.07101,0.06907,0.0001,1.0000,0.0139 -7.750,-0.5325,0.06540,0.06348,-0.0047,1.0000,0.0139 -7.500,-0.5435,0.06066,0.05870,-0.0073,1.0000,0.0139 -7.250,-0.5930,0.06510,0.06288,-0.0095,1.0000,0.0138 -7.000,-0.5862,0.06002,0.05767,-0.0112,1.0000,0.0139 -6.750,-0.5782,0.05504,0.05252,-0.0121,1.0000,0.0139 -6.500,-0.5685,0.05035,0.04762,-0.0124,1.0000,0.0140 -6.250,-0.5764,0.04034,0.03725,-0.0129,1.0000,0.0151 -6.000,-0.5612,0.03849,0.03534,-0.0129,1.0000,0.0163 -5.750,-0.5431,0.03651,0.03324,-0.0127,1.0000,0.0183 -5.500,-0.5242,0.03318,0.02964,-0.0119,1.0000,0.0200 -5.250,-0.4963,0.03258,0.02875,-0.0107,1.0000,0.0232 -5.000,-0.4748,0.03059,0.02644,-0.0095,1.0000,0.0236 -4.750,-0.4637,0.02341,0.01869,-0.0082,1.0000,0.0254 -4.500,-0.4392,0.01853,0.01322,-0.0056,1.0000,0.0147 -4.250,-0.4156,0.01597,0.01042,-0.0044,1.0000,0.0127 -4.000,-0.3918,0.01395,0.00811,-0.0031,1.0000,0.0126 -3.750,-0.3679,0.01266,0.00668,-0.0019,1.0000,0.0132 -3.500,-0.3439,0.01188,0.00580,-0.0009,1.0000,0.0141 -3.250,-0.3237,0.01032,0.00413,0.0007,1.0000,0.0167 -3.000,-0.3008,0.00972,0.00349,0.0017,1.0000,0.0186 -2.750,-0.2779,0.00920,0.00290,0.0029,1.0000,0.0215 -2.500,-0.2518,0.00847,0.00223,0.0033,0.9983,0.0523 -2.250,-0.2149,0.00763,0.00193,0.0007,0.9897,0.1850 -2.000,-0.1808,0.00640,0.00167,-0.0015,0.9797,0.4441 -1.750,-0.1543,0.00518,0.00161,-0.0014,0.9634,0.7487 -1.500,-0.1240,0.00494,0.00161,-0.0013,0.9437,0.8403 -1.250,-0.0964,0.00487,0.00156,-0.0006,0.9180,0.8825 -1.000,-0.0716,0.00490,0.00154,0.0008,0.8891,0.9160 -0.750,-0.0452,0.00499,0.00152,0.0017,0.8595,0.9378 -0.500,-0.0166,0.00510,0.00149,0.0020,0.8299,0.9540 -0.250,0.0171,0.00524,0.00147,0.0011,0.8006,0.9670 0.000,0.0593,0.00539,0.00147,-0.0017,0.7714,0.9760 0.250,0.1102,0.00559,0.00150,-0.0064,0.7414,0.9863 0.500,0.1532,0.00573,0.00149,-0.0097,0.7121,0.9935 0.750,0.1913,0.00580,0.00143,-0.0120,0.6837,0.9976 1.000,0.2234,0.00587,0.00137,-0.0130,0.6560,1.0000 1.250,0.2463,0.00592,0.00133,-0.0121,0.6306,1.0000 1.500,0.2696,0.00599,0.00131,-0.0113,0.6077,1.0000 1.750,0.2932,0.00606,0.00131,-0.0105,0.5865,1.0000 2.000,0.3169,0.00615,0.00135,-0.0098,0.5647,1.0000 2.250,0.3407,0.00625,0.00139,-0.0090,0.5433,1.0000 2.500,0.3646,0.00638,0.00145,-0.0083,0.5205,1.0000 2.750,0.3888,0.00650,0.00152,-0.0076,0.4979,1.0000 3.000,0.4130,0.00664,0.00161,-0.0069,0.4754,1.0000 3.250,0.4373,0.00680,0.00174,-0.0062,0.4521,1.0000 3.500,0.4617,0.00698,0.00187,-0.0056,0.4258,1.0000 3.750,0.4857,0.00724,0.00199,-0.0049,0.3801,1.0000 4.000,0.5090,0.00763,0.00215,-0.0042,0.3177,1.0000 4.250,0.5326,0.00806,0.00237,-0.0036,0.2581,1.0000 4.500,0.5526,0.00919,0.00285,-0.0028,0.1154,1.0000 4.750,0.5723,0.01070,0.00394,-0.0015,0.0182,1.0000 5.000,0.5963,0.01130,0.00466,-0.0007,0.0155,1.0000 5.250,0.6199,0.01196,0.00540,0.0001,0.0133,1.0000 5.500,0.6405,0.01328,0.00686,0.0013,0.0110,1.0000 5.750,0.6609,0.01480,0.00852,0.0026,0.0102,1.0000 6.000,0.6838,0.01590,0.00974,0.0036,0.0096,1.0000 6.250,0.7056,0.01760,0.01162,0.0048,0.0094,1.0000 6.500,0.7269,0.02001,0.01425,0.0061,0.0097,1.0000 6.750,0.7495,0.02229,0.01667,0.0072,0.0112,1.0000 7.250,0.7925,0.03000,0.02524,0.0109,0.0204,1.0000 7.500,0.7889,0.03937,0.03521,0.0121,0.0186,1.0000 7.750,0.8005,0.04233,0.03849,0.0132,0.0185,1.0000 8.000,0.8232,0.04133,0.03777,0.0145,0.0171,1.0000 8.250,0.8346,0.04408,0.04081,0.0156,0.0159,1.0000 8.500,0.8391,0.04768,0.04468,0.0164,0.0151,1.0000 8.750,0.8385,0.05150,0.04874,0.0170,0.0146,1.0000 9.000,0.8316,0.05557,0.05301,0.0173,0.0142,1.0000 9.250,0.8167,0.05930,0.05689,0.0178,0.0142,1.0000 9.500,0.7954,0.06389,0.06160,0.0156,0.0144,1.0000 9.750,0.7731,0.07118,0.06899,0.0089,0.0149,1.0000 10.000,0.7536,0.08181,0.07968,-0.0002,0.0158,1.0000