Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-hq07-il-100000-n5 Airfoil,hq07-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,31.361 Max Cl/Cd alpha,3.25 Url,http://www.airfoiltools.com/polar/csv?polar=xf-hq07-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.6682,0.08759,0.08286,0.0050,1.0000,0.0125 -8.750,-0.6738,0.08131,0.07664,0.0004,1.0000,0.0122 -8.500,-0.6837,0.07408,0.06944,-0.0060,1.0000,0.0119 -8.250,-0.6959,0.06802,0.06330,-0.0093,1.0000,0.0115 -8.000,-0.7029,0.06213,0.05726,-0.0114,1.0000,0.0112 -7.750,-0.7056,0.05664,0.05152,-0.0125,1.0000,0.0109 -7.500,-0.7040,0.05145,0.04603,-0.0128,1.0000,0.0107 -7.250,-0.6982,0.04662,0.04081,-0.0127,1.0000,0.0106 -7.000,-0.6889,0.04215,0.03590,-0.0122,1.0000,0.0105 -6.750,-0.6761,0.03805,0.03131,-0.0114,1.0000,0.0105 -6.500,-0.6605,0.03426,0.02701,-0.0106,1.0000,0.0107 -6.250,-0.6424,0.03090,0.02316,-0.0097,1.0000,0.0111 -6.000,-0.6217,0.02803,0.01986,-0.0088,1.0000,0.0117 -5.750,-0.5993,0.02554,0.01699,-0.0079,1.0000,0.0127 -5.500,-0.5755,0.02390,0.01505,-0.0071,1.0000,0.0165 -5.250,-0.5521,0.02221,0.01312,-0.0064,1.0000,0.0227 -5.000,-0.5282,0.02092,0.01163,-0.0057,1.0000,0.0333 -4.750,-0.5058,0.01917,0.00982,-0.0046,1.0000,0.0392 -4.500,-0.4829,0.01790,0.00835,-0.0035,1.0000,0.0448 -4.250,-0.4598,0.01695,0.00731,-0.0028,1.0000,0.0563 -4.000,-0.4371,0.01592,0.00633,-0.0020,1.0000,0.0739 -3.750,-0.4147,0.01481,0.00528,-0.0012,1.0000,0.1159 -3.500,-0.3948,0.01346,0.00465,-0.0004,1.0000,0.2605 -3.250,-0.3783,0.01205,0.00433,0.0013,1.0000,0.4791 -3.000,-0.3602,0.01148,0.00433,0.0038,1.0000,0.6284 -2.750,-0.3401,0.01127,0.00428,0.0061,1.0000,0.7075 -2.500,-0.3203,0.01114,0.00425,0.0086,1.0000,0.7659 -2.250,-0.2995,0.01104,0.00415,0.0106,1.0000,0.8046 -2.000,-0.2765,0.01094,0.00398,0.0119,1.0000,0.8282 -1.750,-0.2530,0.01084,0.00381,0.0130,1.0000,0.8500 -1.500,-0.2283,0.01077,0.00360,0.0139,1.0000,0.8747 -1.250,-0.1984,0.01075,0.00356,0.0139,1.0000,0.9035 -1.000,-0.1614,0.01076,0.00353,0.0122,1.0000,0.9309 -0.750,-0.1216,0.01075,0.00347,0.0095,1.0000,0.9512 -0.500,-0.0814,0.01074,0.00340,0.0066,1.0000,0.9680 -0.250,-0.0401,0.01071,0.00335,0.0033,1.0000,0.9827 0.000,0.0000,0.01069,0.00332,0.0000,1.0000,1.0000 0.250,0.0401,0.01070,0.00334,-0.0033,0.9827,1.0000 0.500,0.0814,0.01073,0.00340,-0.0066,0.9680,1.0000 0.750,0.1215,0.01075,0.00347,-0.0095,0.9511,1.0000 1.000,0.1614,0.01075,0.00352,-0.0122,0.9308,1.0000 1.250,0.1982,0.01075,0.00356,-0.0138,0.9035,1.0000 1.500,0.2279,0.01077,0.00360,-0.0139,0.8747,1.0000 1.750,0.2526,0.01084,0.00380,-0.0129,0.8499,1.0000 2.000,0.2761,0.01094,0.00397,-0.0119,0.8282,1.0000 2.250,0.2990,0.01104,0.00415,-0.0106,0.8047,1.0000 2.500,0.3199,0.01114,0.00424,-0.0085,0.7663,1.0000 2.750,0.3396,0.01127,0.00428,-0.0060,0.7078,1.0000 3.000,0.3598,0.01148,0.00433,-0.0037,0.6298,1.0000 3.250,0.3779,0.01205,0.00433,-0.0012,0.4796,1.0000 3.500,0.3943,0.01348,0.00466,0.0005,0.2580,1.0000 3.750,0.4145,0.01480,0.00527,0.0012,0.1165,1.0000 4.000,0.4369,0.01592,0.00633,0.0020,0.0740,1.0000 4.250,0.4598,0.01695,0.00731,0.0028,0.0564,1.0000 4.500,0.4829,0.01791,0.00835,0.0035,0.0447,1.0000 4.750,0.5058,0.01919,0.00984,0.0046,0.0391,1.0000 5.000,0.5285,0.02090,0.01162,0.0057,0.0336,1.0000 5.250,0.5523,0.02222,0.01313,0.0063,0.0227,1.0000 5.500,0.5757,0.02391,0.01505,0.0071,0.0165,1.0000 5.750,0.5996,0.02557,0.01701,0.0078,0.0127,1.0000 6.000,0.6220,0.02805,0.01987,0.0087,0.0116,1.0000 6.250,0.6427,0.03092,0.02318,0.0096,0.0110,1.0000 6.500,0.6611,0.03429,0.02705,0.0105,0.0107,1.0000 6.750,0.6766,0.03809,0.03136,0.0113,0.0105,1.0000 7.000,0.6892,0.04225,0.03600,0.0120,0.0105,1.0000 7.250,0.6989,0.04669,0.04089,0.0125,0.0106,1.0000 7.500,0.7045,0.05152,0.04610,0.0126,0.0107,1.0000 7.750,0.7064,0.05678,0.05168,0.0122,0.0110,1.0000 8.000,0.7039,0.06223,0.05736,0.0112,0.0112,1.0000 8.250,0.6967,0.06818,0.06347,0.0090,0.0115,1.0000 8.500,0.6844,0.07427,0.06963,0.0056,0.0119,1.0000 8.750,0.6750,0.08136,0.07668,-0.0007,0.0121,1.0000 9.000,0.6695,0.08765,0.08292,-0.0053,0.0124,1.0000