Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-hq259-il-1000000 Airfoil,hq259-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,122.004 Max Cl/Cd alpha,3 Url,http://airfoiltools.com/polar/csv?polar=xf-hq259-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.4089,0.08265,0.08110,-0.0336,1.0000,0.0073 -8.250,-0.4106,0.07901,0.07749,-0.0349,1.0000,0.0072 -8.000,-0.4161,0.07542,0.07394,-0.0359,1.0000,0.0073 -7.750,-0.4306,0.07272,0.07130,-0.0348,1.0000,0.0073 -7.500,-0.4191,0.06578,0.06436,-0.0457,0.9959,0.0073 -7.250,-0.3968,0.05618,0.05465,-0.0610,0.9884,0.0075 -7.000,-0.3719,0.04828,0.04657,-0.0706,0.9837,0.0080 -6.750,-0.3442,0.04212,0.04021,-0.0764,0.9788,0.0087 -6.500,-0.3141,0.03829,0.03620,-0.0791,0.9729,0.0092 -6.250,-0.2902,0.03309,0.03070,-0.0819,0.9646,0.0093 -6.000,-0.2922,0.01648,0.01253,-0.0812,0.9451,0.0055 -5.750,-0.2711,0.01364,0.00930,-0.0804,0.9360,0.0062 -5.500,-0.2455,0.01303,0.00858,-0.0801,0.9284,0.0068 -5.250,-0.2201,0.01220,0.00761,-0.0797,0.9202,0.0073 -5.000,-0.1945,0.01132,0.00657,-0.0792,0.9128,0.0076 -4.750,-0.1689,0.01052,0.00564,-0.0787,0.9050,0.0079 -4.500,-0.1427,0.00996,0.00497,-0.0784,0.8979,0.0084 -4.250,-0.1162,0.00950,0.00441,-0.0780,0.8905,0.0089 -4.000,-0.0900,0.00886,0.00364,-0.0777,0.8834,0.0091 -3.750,-0.0632,0.00841,0.00309,-0.0774,0.8761,0.0093 -3.500,-0.0366,0.00770,0.00220,-0.0770,0.8689,0.0128 -3.250,-0.0094,0.00741,0.00189,-0.0767,0.8614,0.0226 -3.000,0.0180,0.00720,0.00172,-0.0766,0.8532,0.0414 -2.750,0.0452,0.00706,0.00157,-0.0765,0.8454,0.0564 -2.500,0.0728,0.00688,0.00143,-0.0765,0.8374,0.0770 -2.250,0.0998,0.00653,0.00129,-0.0765,0.8303,0.1476 -2.000,0.1257,0.00582,0.00112,-0.0766,0.8227,0.3232 -1.750,0.1519,0.00531,0.00102,-0.0766,0.8152,0.4756 -1.500,0.1789,0.00512,0.00098,-0.0764,0.8065,0.5458 -1.250,0.2064,0.00503,0.00095,-0.0763,0.7966,0.5878 -1.000,0.2339,0.00498,0.00093,-0.0762,0.7864,0.6168 -0.750,0.2612,0.00495,0.00091,-0.0760,0.7758,0.6487 -0.500,0.2886,0.00494,0.00091,-0.0758,0.7654,0.6724 -0.250,0.3161,0.00491,0.00092,-0.0757,0.7558,0.6996 0.000,0.3433,0.00490,0.00095,-0.0755,0.7462,0.7265 0.250,0.3707,0.00492,0.00096,-0.0753,0.7353,0.7422 0.500,0.3981,0.00495,0.00097,-0.0751,0.7231,0.7555 0.750,0.4256,0.00498,0.00098,-0.0750,0.7109,0.7661 1.000,0.4532,0.00501,0.00099,-0.0749,0.6984,0.7767 1.250,0.4805,0.00504,0.00103,-0.0748,0.6854,0.7876 1.500,0.5075,0.00509,0.00106,-0.0745,0.6701,0.7992 1.750,0.5343,0.00515,0.00110,-0.0743,0.6522,0.8118 2.000,0.5610,0.00521,0.00114,-0.0740,0.6329,0.8259 2.250,0.5873,0.00528,0.00120,-0.0737,0.6132,0.8425 2.500,0.6127,0.00535,0.00128,-0.0732,0.5880,0.8637 2.750,0.6363,0.00539,0.00135,-0.0722,0.5602,0.9025 3.000,0.6698,0.00549,0.00143,-0.0735,0.5224,1.0000 3.250,0.6951,0.00581,0.00156,-0.0731,0.4787,1.0000 3.500,0.7200,0.00617,0.00174,-0.0727,0.4312,1.0000 3.750,0.7449,0.00654,0.00192,-0.0723,0.3864,1.0000 4.000,0.7702,0.00688,0.00211,-0.0720,0.3479,1.0000 4.250,0.7941,0.00736,0.00234,-0.0715,0.2946,1.0000 4.500,0.8182,0.00781,0.00259,-0.0710,0.2508,1.0000 4.750,0.8430,0.00820,0.00284,-0.0706,0.2166,1.0000 5.000,0.8672,0.00865,0.00310,-0.0702,0.1786,1.0000 5.250,0.8915,0.00907,0.00337,-0.0697,0.1456,1.0000 5.500,0.9151,0.00958,0.00369,-0.0692,0.1106,1.0000 5.750,0.9346,0.01057,0.00427,-0.0680,0.0434,1.0000 6.000,0.9549,0.01150,0.00497,-0.0669,0.0063,1.0000 6.250,0.9799,0.01185,0.00539,-0.0664,0.0056,1.0000 6.500,1.0044,0.01226,0.00585,-0.0659,0.0050,1.0000 6.750,1.0282,0.01274,0.00639,-0.0653,0.0044,1.0000 7.000,1.0494,0.01359,0.00737,-0.0641,0.0036,1.0000 7.500,1.0883,0.01560,0.00965,-0.0613,0.0033,1.0000 7.750,1.1069,0.01664,0.01080,-0.0598,0.0033,1.0000 8.000,1.1225,0.01802,0.01232,-0.0579,0.0033,1.0000 8.250,1.1375,0.01955,0.01396,-0.0559,0.0034,1.0000 8.500,1.1570,0.02044,0.01494,-0.0547,0.0035,1.0000 8.750,1.1763,0.02133,0.01591,-0.0534,0.0036,1.0000 9.000,1.1954,0.02221,0.01690,-0.0521,0.0038,1.0000 17.250,0.9703,0.22187,0.22037,-0.1097,0.0061,1.0000 17.500,0.9783,0.22607,0.22457,-0.1120,0.0059,1.0000