Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-n63010a-il-100000 Airfoil,n63010a-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,37.6802 Max Cl/Cd alpha,4 Url,http://airfoiltools.com/polar/csv?polar=xf-n63010a-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.750,-0.5333,0.09589,0.09126,-0.0031,1.0000,0.1582 -9.500,-0.5678,0.08998,0.08545,-0.0083,1.0000,0.1640 -9.250,-0.7092,0.09003,0.08540,-0.0081,1.0000,0.1499 -9.000,-0.6843,0.08783,0.08316,-0.0023,1.0000,0.1560 -8.750,-0.7103,0.08144,0.07684,-0.0094,1.0000,0.1625 -7.500,-0.7593,0.04430,0.03682,-0.0146,1.0000,0.0698 -7.250,-0.7406,0.04136,0.03354,-0.0132,1.0000,0.0682 -7.000,-0.7239,0.03769,0.02954,-0.0119,1.0000,0.0677 -6.750,-0.7050,0.03416,0.02569,-0.0107,1.0000,0.0662 -6.500,-0.6840,0.03122,0.02236,-0.0093,1.0000,0.0652 -6.250,-0.6612,0.02874,0.01949,-0.0081,1.0000,0.0653 -6.000,-0.6370,0.02666,0.01711,-0.0070,1.0000,0.0665 -5.750,-0.6129,0.02480,0.01502,-0.0060,1.0000,0.0702 -5.500,-0.5888,0.02298,0.01327,-0.0053,1.0000,0.0747 -5.250,-0.5648,0.02153,0.01176,-0.0041,1.0000,0.0796 -5.000,-0.5441,0.01997,0.01029,-0.0027,1.0000,0.0869 -4.750,-0.5257,0.01873,0.00916,-0.0010,1.0000,0.1011 -4.500,-0.5097,0.01737,0.00797,0.0011,1.0000,0.1256 -4.250,-0.5073,0.01422,0.00655,0.0046,1.0000,0.3556 -4.000,-0.5020,0.01332,0.00688,0.0102,1.0000,0.6258 -3.750,-0.4854,0.01342,0.00706,0.0136,1.0000,0.6908 -3.500,-0.4684,0.01359,0.00721,0.0168,1.0000,0.7354 -3.250,-0.4516,0.01380,0.00744,0.0204,1.0000,0.7717 -3.000,-0.4367,0.01406,0.00771,0.0245,1.0000,0.8070 -2.750,-0.4225,0.01435,0.00800,0.0289,1.0000,0.8400 -2.500,-0.4055,0.01458,0.00816,0.0324,1.0000,0.8682 -2.250,-0.3785,0.01479,0.00828,0.0337,1.0000,0.8894 -2.000,-0.3487,0.01485,0.00822,0.0335,1.0000,0.9091 -1.750,-0.3135,0.01489,0.00813,0.0319,1.0000,0.9264 -1.500,-0.2686,0.01495,0.00805,0.0282,1.0000,0.9404 -1.250,-0.2145,0.01500,0.00798,0.0226,1.0000,0.9512 -1.000,-0.1590,0.01500,0.00786,0.0164,1.0000,0.9616 -0.750,-0.1070,0.01494,0.00774,0.0106,1.0000,0.9731 -0.500,-0.0550,0.01485,0.00762,0.0047,1.0000,0.9847 -0.250,-0.0016,0.01474,0.00748,-0.0018,1.0000,0.9957 0.000,0.0000,0.01472,0.00746,0.0000,1.0000,1.0000 0.250,0.0016,0.01474,0.00748,0.0018,0.9958,1.0000 0.500,0.0550,0.01485,0.00762,-0.0047,0.9847,1.0000 0.750,0.1069,0.01494,0.00774,-0.0106,0.9731,1.0000 1.000,0.1590,0.01499,0.00786,-0.0164,0.9616,1.0000 1.250,0.2145,0.01500,0.00798,-0.0226,0.9513,1.0000 1.500,0.2686,0.01494,0.00804,-0.0282,0.9404,1.0000 1.750,0.3135,0.01488,0.00813,-0.0319,0.9264,1.0000 2.000,0.3486,0.01485,0.00822,-0.0335,0.9091,1.0000 2.250,0.3784,0.01479,0.00827,-0.0336,0.8894,1.0000 2.500,0.4054,0.01458,0.00816,-0.0324,0.8682,1.0000 2.750,0.4224,0.01435,0.00799,-0.0288,0.8400,1.0000 3.000,0.4366,0.01406,0.00771,-0.0244,0.8071,1.0000 3.250,0.4514,0.01380,0.00744,-0.0203,0.7717,1.0000 3.500,0.4682,0.01359,0.00721,-0.0168,0.7355,1.0000 3.750,0.4853,0.01342,0.00706,-0.0135,0.6910,1.0000 4.000,0.5019,0.01332,0.00688,-0.0101,0.6260,1.0000 4.250,0.5073,0.01421,0.00655,-0.0046,0.3576,1.0000 4.500,0.5095,0.01736,0.00796,-0.0011,0.1257,1.0000 4.750,0.5256,0.01873,0.00916,0.0010,0.1011,1.0000 5.000,0.5440,0.01997,0.01029,0.0027,0.0870,1.0000 5.250,0.5647,0.02153,0.01175,0.0042,0.0796,1.0000 5.500,0.5887,0.02297,0.01327,0.0053,0.0747,1.0000 5.750,0.6128,0.02479,0.01501,0.0060,0.0702,1.0000 6.000,0.6369,0.02666,0.01710,0.0070,0.0664,1.0000 6.250,0.6611,0.02874,0.01949,0.0081,0.0652,1.0000 6.500,0.6840,0.03122,0.02236,0.0093,0.0652,1.0000 6.750,0.7050,0.03417,0.02569,0.0107,0.0662,1.0000 7.000,0.7239,0.03770,0.02954,0.0119,0.0677,1.0000 7.250,0.7406,0.04137,0.03356,0.0132,0.0682,1.0000 7.500,0.7594,0.04430,0.03683,0.0146,0.0698,1.0000 9.000,0.6854,0.08781,0.08313,0.0023,0.1559,1.0000 9.250,0.7087,0.09015,0.08552,0.0077,0.1498,1.0000 9.500,0.6706,0.09782,0.09303,-0.0036,0.1433,1.0000 9.750,0.7220,0.09830,0.09363,0.0086,0.1367,1.0000