Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-hq07-il-100000 Airfoil,hq07-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,35.0551 Max Cl/Cd alpha,3.5 Url,http://www.airfoiltools.com/polar/csv?polar=xf-hq07-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.6680,0.08692,0.08246,0.0041,1.0000,0.1042 -8.000,-0.6793,0.08215,0.07774,-0.0006,1.0000,0.1076 -7.750,-0.6925,0.07691,0.07241,-0.0064,1.0000,0.1097 -7.500,-0.7095,0.07305,0.06815,-0.0115,1.0000,0.1111 -6.000,-0.6267,0.03751,0.03037,-0.0120,1.0000,0.0566 -5.750,-0.6064,0.03280,0.02518,-0.0109,1.0000,0.0524 -5.500,-0.5833,0.02891,0.02063,-0.0095,1.0000,0.0507 -5.250,-0.5588,0.02673,0.01795,-0.0084,1.0000,0.0570 -5.000,-0.5339,0.02372,0.01451,-0.0074,1.0000,0.0621 -4.750,-0.5077,0.02172,0.01229,-0.0065,1.0000,0.0696 -4.500,-0.4828,0.01984,0.01038,-0.0057,1.0000,0.0801 -4.250,-0.4584,0.01806,0.00860,-0.0045,1.0000,0.0881 -4.000,-0.4364,0.01653,0.00718,-0.0032,1.0000,0.1045 -3.750,-0.4170,0.01467,0.00589,-0.0019,1.0000,0.1712 -3.500,-0.4133,0.01179,0.00545,0.0029,1.0000,0.6198 -3.250,-0.3986,0.01165,0.00557,0.0073,1.0000,0.7396 -3.000,-0.3842,0.01169,0.00569,0.0120,1.0000,0.8086 -2.750,-0.3684,0.01177,0.00567,0.0166,1.0000,0.8605 -2.500,-0.3375,0.01208,0.00584,0.0187,1.0000,0.9087 -2.250,-0.2791,0.01240,0.00584,0.0143,1.0000,0.9423 -2.000,-0.2189,0.01236,0.00551,0.0079,1.0000,0.9575 -1.750,-0.1578,0.01220,0.00505,0.0010,1.0000,0.9731 -1.500,-0.0839,0.01190,0.00455,-0.0085,1.0000,0.9947 -1.250,-0.0515,0.01155,0.00413,-0.0107,1.0000,1.0000 -1.000,-0.0354,0.01129,0.00385,-0.0096,1.0000,1.0000 -0.750,-0.0206,0.01106,0.00363,-0.0083,1.0000,1.0000 -0.500,-0.0084,0.01087,0.00346,-0.0065,1.0000,1.0000 -0.250,-0.0011,0.01074,0.00336,-0.0038,1.0000,1.0000 0.000,0.0000,0.01068,0.00333,0.0000,1.0000,1.0000 0.250,0.0011,0.01074,0.00336,0.0038,1.0000,1.0000 0.500,0.0084,0.01087,0.00346,0.0065,1.0000,1.0000 0.750,0.0206,0.01106,0.00363,0.0083,1.0000,1.0000 1.000,0.0354,0.01129,0.00385,0.0096,1.0000,1.0000 1.250,0.0515,0.01155,0.00414,0.0107,1.0000,1.0000 1.500,0.0836,0.01190,0.00454,0.0086,0.9947,1.0000 1.750,0.1578,0.01220,0.00505,-0.0010,0.9731,1.0000 2.000,0.2190,0.01236,0.00551,-0.0079,0.9575,1.0000 2.250,0.2791,0.01240,0.00584,-0.0143,0.9423,1.0000 2.500,0.3375,0.01208,0.00584,-0.0187,0.9087,1.0000 2.750,0.3684,0.01177,0.00567,-0.0165,0.8604,1.0000 3.000,0.3842,0.01169,0.00569,-0.0120,0.8086,1.0000 3.250,0.3986,0.01165,0.00557,-0.0073,0.7396,1.0000 3.500,0.4133,0.01179,0.00545,-0.0029,0.6196,1.0000 3.750,0.4169,0.01469,0.00589,0.0019,0.1701,1.0000 4.000,0.4364,0.01653,0.00718,0.0032,0.1046,1.0000 4.250,0.4584,0.01805,0.00860,0.0045,0.0882,1.0000 4.500,0.4828,0.01985,0.01039,0.0057,0.0801,1.0000 4.750,0.5077,0.02173,0.01229,0.0065,0.0696,1.0000 5.000,0.5340,0.02372,0.01451,0.0074,0.0622,1.0000 5.250,0.5589,0.02673,0.01795,0.0084,0.0571,1.0000 5.500,0.5833,0.02892,0.02063,0.0095,0.0506,1.0000 5.750,0.6065,0.03280,0.02518,0.0109,0.0524,1.0000 6.000,0.6268,0.03747,0.03034,0.0120,0.0566,1.0000 6.250,0.6545,0.05318,0.04838,0.0089,0.1842,1.0000 6.500,0.6675,0.05662,0.05184,0.0096,0.1672,1.0000 6.750,0.6797,0.06033,0.05555,0.0103,0.1526,1.0000 8.000,0.7102,0.08108,0.07643,0.0090,0.0977,1.0000 8.250,0.6931,0.08551,0.08103,0.0038,0.0971,1.0000 8.500,0.6806,0.09047,0.08599,-0.0011,0.0968,1.0000