Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-tsagi8-il-100000 Airfoil,tsagi8-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,45.2917 Max Cl/Cd alpha,4.75 Url,http://airfoiltools.com/polar/csv?polar=xf-tsagi8-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.5619,0.09918,0.09438,-0.0066,1.0000,0.0914 -8.750,-0.5779,0.09546,0.09075,-0.0127,1.0000,0.0924 -8.500,-0.5994,0.09231,0.08762,-0.0169,1.0000,0.0928 -8.250,-0.5655,0.08684,0.08219,-0.0113,1.0000,0.0976 -8.000,-0.5688,0.08330,0.07868,-0.0124,1.0000,0.1009 -7.750,-0.4934,0.07001,0.06572,-0.0152,1.0000,0.1133 -7.500,-0.5068,0.06602,0.06176,-0.0164,1.0000,0.1163 -7.250,-0.5357,0.06190,0.05749,-0.0200,1.0000,0.1200 -7.000,-0.5245,0.05668,0.05236,-0.0185,1.0000,0.1237 -6.750,-0.5772,0.06388,0.05906,-0.0175,1.0000,0.1234 -6.500,-0.5800,0.06184,0.05663,-0.0175,1.0000,0.1348 -6.250,-0.5623,0.05710,0.05215,-0.0159,1.0000,0.1394 -6.000,-0.5551,0.05401,0.04897,-0.0148,1.0000,0.1528 -5.750,-0.5457,0.05131,0.04620,-0.0132,1.0000,0.1692 -5.500,-0.5402,0.04872,0.04344,-0.0115,1.0000,0.1919 -5.250,-0.5285,0.04581,0.04055,-0.0095,1.0000,0.2079 -5.000,-0.5014,0.03472,0.02744,-0.0074,1.0000,0.0771 -4.750,-0.4837,0.03135,0.02317,-0.0038,1.0000,0.0659 -4.500,-0.4656,0.02796,0.01952,-0.0019,1.0000,0.0644 -4.250,-0.4455,0.02552,0.01668,0.0001,1.0000,0.0643 -4.000,-0.4252,0.02347,0.01431,0.0019,1.0000,0.0683 -3.750,-0.4033,0.02176,0.01251,0.0032,1.0000,0.0726 -3.500,-0.3798,0.02021,0.01073,0.0048,1.0000,0.0771 -3.250,-0.3585,0.01882,0.00936,0.0062,1.0000,0.0860 -3.000,-0.3385,0.01762,0.00816,0.0078,1.0000,0.0979 -2.750,-0.0974,0.01299,0.00641,-0.0289,1.0000,1.0000 -2.500,-0.0795,0.01278,0.00602,-0.0275,1.0000,1.0000 -2.250,-0.0620,0.01261,0.00570,-0.0261,1.0000,1.0000 -2.000,-0.0451,0.01248,0.00545,-0.0245,1.0000,1.0000 -1.750,-0.0294,0.01239,0.00527,-0.0227,1.0000,1.0000 -1.500,-0.0154,0.01235,0.00514,-0.0206,1.0000,1.0000 -1.250,-0.0042,0.01239,0.00513,-0.0181,1.0000,1.0000 -1.000,0.0012,0.01255,0.00526,-0.0147,1.0000,1.0000 -0.750,-0.0014,0.01287,0.00555,-0.0102,1.0000,1.0000 -0.500,-0.0062,0.01331,0.00594,-0.0057,1.0000,1.0000 -0.250,0.0447,0.01349,0.00605,-0.0114,0.9882,1.0000 0.000,0.1038,0.01357,0.00606,-0.0184,0.9742,1.0000 0.250,0.1626,0.01355,0.00602,-0.0251,0.9606,1.0000 0.500,0.2218,0.01344,0.00592,-0.0317,0.9469,1.0000 0.750,0.2758,0.01328,0.00579,-0.0370,0.9308,1.0000 1.000,0.3248,0.01310,0.00565,-0.0411,0.9130,1.0000 1.250,0.3597,0.01305,0.00565,-0.0423,0.8899,1.0000 1.500,0.3894,0.01305,0.00566,-0.0422,0.8677,1.0000 1.750,0.4139,0.01313,0.00574,-0.0411,0.8454,1.0000 2.000,0.4358,0.01327,0.00589,-0.0395,0.8234,1.0000 2.250,0.4573,0.01342,0.00608,-0.0377,0.8029,1.0000 2.500,0.4782,0.01361,0.00630,-0.0359,0.7817,1.0000 2.750,0.4994,0.01380,0.00651,-0.0342,0.7617,1.0000 3.000,0.5206,0.01401,0.00676,-0.0324,0.7413,1.0000 3.250,0.5418,0.01421,0.00701,-0.0307,0.7207,1.0000 3.500,0.5633,0.01442,0.00732,-0.0289,0.7001,1.0000 3.750,0.5846,0.01460,0.00758,-0.0272,0.6782,1.0000 4.000,0.6042,0.01463,0.00761,-0.0246,0.6491,1.0000 4.250,0.6201,0.01438,0.00727,-0.0209,0.5998,1.0000 4.500,0.6367,0.01429,0.00710,-0.0177,0.5450,1.0000 4.750,0.6522,0.01440,0.00708,-0.0146,0.4655,1.0000 5.000,0.6485,0.01730,0.00789,-0.0093,0.1223,1.0000 5.250,0.6600,0.01930,0.00955,-0.0065,0.0842,1.0000 5.500,0.6746,0.02077,0.01098,-0.0041,0.0707,1.0000 5.750,0.6926,0.02209,0.01237,-0.0019,0.0646,1.0000 6.000,0.7118,0.02399,0.01413,-0.0002,0.0601,1.0000 6.250,0.7341,0.02575,0.01603,0.0012,0.0557,1.0000 6.500,0.7570,0.02758,0.01803,0.0026,0.0527,1.0000 6.750,0.7800,0.02997,0.02073,0.0041,0.0519,1.0000 7.000,0.8008,0.03270,0.02388,0.0059,0.0527,1.0000 7.250,0.8187,0.03589,0.02752,0.0080,0.0546,1.0000 7.500,0.8337,0.03952,0.03153,0.0101,0.0566,1.0000 7.750,0.8453,0.04305,0.03545,0.0123,0.0572,1.0000 8.000,0.8546,0.04702,0.03974,0.0143,0.0579,1.0000 8.250,0.8585,0.05185,0.04534,0.0178,0.0697,1.0000 10.500,0.7012,0.11027,0.10521,0.0018,0.1497,1.0000 10.750,0.7209,0.11310,0.10811,0.0055,0.1372,1.0000 11.000,0.6891,0.11866,0.11353,-0.0021,0.1353,1.0000