Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-hq09-il-50000 Airfoil,hq09-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,27.2647 Max Cl/Cd alpha,4.25 Url,http://airfoiltools.com/polar/csv?polar=xf-hq09-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.500,-0.6630,0.05546,0.04929,-0.0137,1.0000,0.1482 -7.250,-0.6693,0.04795,0.04141,-0.0153,1.0000,0.1345 -7.000,-0.7097,0.05257,0.04475,-0.0148,1.0000,0.1221 -6.750,-0.6941,0.04753,0.03944,-0.0144,1.0000,0.1180 -6.500,-0.6791,0.04274,0.03401,-0.0137,1.0000,0.1144 -6.250,-0.6601,0.03869,0.02935,-0.0128,1.0000,0.1140 -6.000,-0.6396,0.03579,0.02582,-0.0117,1.0000,0.1217 -5.750,-0.6159,0.03261,0.02233,-0.0109,1.0000,0.1277 -5.500,-0.5894,0.02984,0.01912,-0.0099,1.0000,0.1336 -5.250,-0.5621,0.02735,0.01649,-0.0091,1.0000,0.1438 -5.000,-0.5372,0.02551,0.01469,-0.0081,1.0000,0.1677 -4.750,-0.5107,0.02345,0.01273,-0.0069,1.0000,0.1989 -4.500,-0.4904,0.02085,0.01082,-0.0052,1.0000,0.2830 -4.250,-0.4925,0.01806,0.01053,0.0026,1.0000,0.5930 -4.000,-0.4856,0.01885,0.01152,0.0118,1.0000,0.7348 -3.750,-0.4656,0.01993,0.01235,0.0193,1.0000,0.8114 -3.500,-0.3490,0.02219,0.01357,0.0128,1.0000,0.9117 -3.250,-0.2594,0.02149,0.01211,0.0014,1.0000,0.9521 -3.000,-0.1776,0.02022,0.01034,-0.0101,1.0000,0.9849 -2.750,-0.1299,0.01916,0.00901,-0.0160,1.0000,1.0000 -2.500,-0.1137,0.01858,0.00834,-0.0158,1.0000,1.0000 -2.250,-0.0973,0.01808,0.00771,-0.0154,1.0000,1.0000 -2.000,-0.0809,0.01763,0.00720,-0.0149,1.0000,1.0000 -1.750,-0.0648,0.01723,0.00676,-0.0142,1.0000,1.0000 -1.500,-0.0491,0.01688,0.00639,-0.0134,1.0000,1.0000 -1.250,-0.0342,0.01658,0.00608,-0.0124,1.0000,1.0000 -1.000,-0.0206,0.01633,0.00584,-0.0110,1.0000,1.0000 -0.750,-0.0092,0.01612,0.00564,-0.0093,1.0000,1.0000 -0.500,-0.0014,0.01596,0.00552,-0.0070,1.0000,1.0000 -0.250,0.0013,0.01586,0.00546,-0.0038,1.0000,1.0000 0.000,0.0000,0.01582,0.00545,0.0000,1.0000,1.0000 0.250,-0.0013,0.01586,0.00546,0.0038,1.0000,1.0000 0.500,0.0014,0.01596,0.00552,0.0070,1.0000,1.0000 0.750,0.0092,0.01612,0.00564,0.0093,1.0000,1.0000 1.000,0.0207,0.01632,0.00583,0.0110,1.0000,1.0000 1.250,0.0343,0.01658,0.00608,0.0124,1.0000,1.0000 1.500,0.0492,0.01688,0.00638,0.0134,1.0000,1.0000 1.750,0.0649,0.01723,0.00675,0.0142,1.0000,1.0000 2.000,0.0811,0.01762,0.00719,0.0149,1.0000,1.0000 2.250,0.0975,0.01807,0.00770,0.0154,1.0000,1.0000 2.500,0.1139,0.01858,0.00833,0.0158,1.0000,1.0000 2.750,0.1302,0.01916,0.00901,0.0160,1.0000,1.0000 3.000,0.1779,0.02021,0.01033,0.0101,0.9849,1.0000 3.250,0.2597,0.02148,0.01210,-0.0014,0.9522,1.0000 3.500,0.3494,0.02218,0.01356,-0.0129,0.9117,1.0000 3.750,0.4656,0.01994,0.01235,-0.0193,0.8117,1.0000 4.000,0.4855,0.01885,0.01152,-0.0118,0.7348,1.0000 4.250,0.4924,0.01806,0.01053,-0.0026,0.5931,1.0000 4.500,0.4904,0.02085,0.01081,0.0052,0.2831,1.0000 4.750,0.5106,0.02344,0.01273,0.0069,0.1990,1.0000 5.000,0.5372,0.02551,0.01469,0.0081,0.1678,1.0000 5.250,0.5621,0.02735,0.01650,0.0091,0.1439,1.0000 5.500,0.5894,0.02985,0.01912,0.0099,0.1336,1.0000 5.750,0.6159,0.03261,0.02234,0.0109,0.1277,1.0000 6.000,0.6397,0.03580,0.02583,0.0117,0.1217,1.0000 6.250,0.6602,0.03870,0.02935,0.0128,0.1140,1.0000 6.500,0.6793,0.04275,0.03403,0.0137,0.1144,1.0000 6.750,0.6943,0.04755,0.03946,0.0143,0.1180,1.0000 7.000,0.7099,0.05259,0.04476,0.0148,0.1221,1.0000 7.250,0.7145,0.05880,0.05172,0.0140,0.1342,1.0000 7.500,0.6635,0.05538,0.04921,0.0137,0.1483,1.0000 7.750,0.6514,0.06461,0.05872,0.0099,0.1766,1.0000 8.000,0.6027,0.07264,0.06677,0.0024,0.1928,1.0000 8.250,0.6040,0.09581,0.08918,-0.0276,0.3627,1.0000