Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-hq07-il-500000 Airfoil,hq07-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,50.2467 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-hq07-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.6514,0.08050,0.07837,-0.0005,1.0000,0.0122 -8.500,-0.6579,0.07352,0.07136,-0.0072,1.0000,0.0122 -8.250,-0.6704,0.06894,0.06671,-0.0096,1.0000,0.0122 -8.000,-0.6780,0.06449,0.06215,-0.0107,1.0000,0.0122 -7.750,-0.6994,0.05600,0.05345,-0.0123,1.0000,0.0125 -7.500,-0.7080,0.04914,0.04633,-0.0128,1.0000,0.0130 -7.250,-0.7047,0.04418,0.04112,-0.0127,1.0000,0.0133 -7.000,-0.6952,0.04003,0.03672,-0.0122,1.0000,0.0136 -6.750,-0.6826,0.03607,0.03247,-0.0115,1.0000,0.0139 -6.500,-0.6649,0.03216,0.02814,-0.0101,1.0000,0.0131 -6.250,-0.6515,0.02634,0.02191,-0.0087,1.0000,0.0091 -6.000,-0.6352,0.01882,0.01342,-0.0058,1.0000,0.0070 -5.750,-0.6122,0.01643,0.01070,-0.0047,1.0000,0.0069 -5.500,-0.5894,0.01450,0.00853,-0.0036,1.0000,0.0071 -5.250,-0.5659,0.01319,0.00708,-0.0027,1.0000,0.0079 -5.000,-0.5412,0.01236,0.00617,-0.0021,1.0000,0.0100 -4.750,-0.5176,0.01123,0.00490,-0.0012,1.0000,0.0162 -4.500,-0.4899,0.01146,0.00516,-0.0012,1.0000,0.0220 -4.250,-0.4662,0.01065,0.00432,-0.0007,1.0000,0.0290 -4.000,-0.4410,0.01017,0.00376,-0.0001,1.0000,0.0318 -3.750,-0.4163,0.00962,0.00313,0.0005,1.0000,0.0367 -3.500,-0.3919,0.00902,0.00258,0.0012,1.0000,0.0555 -3.250,-0.3697,0.00813,0.00216,0.0018,1.0000,0.1551 -3.000,-0.3471,0.00748,0.00187,0.0025,1.0000,0.2580 -2.750,-0.3260,0.00671,0.00164,0.0033,1.0000,0.3947 -2.500,-0.3055,0.00609,0.00150,0.0044,1.0000,0.5197 -2.250,-0.2824,0.00568,0.00150,0.0051,0.9985,0.6331 -2.000,-0.2444,0.00548,0.00149,0.0029,0.9897,0.6967 -1.750,-0.2058,0.00537,0.00144,0.0006,0.9817,0.7343 -1.500,-0.1699,0.00528,0.00142,-0.0010,0.9709,0.7650 -1.250,-0.1351,0.00521,0.00141,-0.0023,0.9583,0.7904 -1.000,-0.1030,0.00518,0.00138,-0.0030,0.9423,0.8060 -0.750,-0.0753,0.00516,0.00135,-0.0028,0.9235,0.8200 -0.500,-0.0494,0.00514,0.00132,-0.0020,0.9053,0.8350 -0.250,-0.0243,0.00512,0.00131,-0.0011,0.8883,0.8508 0.000,0.0000,0.00512,0.00130,0.0000,0.8692,0.8694 0.250,0.0244,0.00512,0.00131,0.0011,0.8507,0.8883 0.500,0.0495,0.00514,0.00132,0.0020,0.8350,0.9053 0.750,0.0753,0.00516,0.00135,0.0027,0.8200,0.9235 1.000,0.1031,0.00518,0.00138,0.0030,0.8060,0.9424 1.250,0.1352,0.00521,0.00141,0.0023,0.7904,0.9582 1.500,0.1699,0.00528,0.00142,0.0010,0.7650,0.9710 1.750,0.2058,0.00537,0.00144,-0.0006,0.7342,0.9818 2.000,0.2445,0.00548,0.00149,-0.0029,0.6971,0.9897 2.250,0.2823,0.00569,0.00150,-0.0051,0.6306,0.9986 2.500,0.3055,0.00608,0.00150,-0.0044,0.5216,1.0000 2.750,0.3259,0.00672,0.00164,-0.0033,0.3934,1.0000 3.000,0.3471,0.00748,0.00187,-0.0025,0.2581,1.0000 3.250,0.3696,0.00813,0.00216,-0.0018,0.1551,1.0000 3.500,0.3918,0.00902,0.00259,-0.0012,0.0552,1.0000 3.750,0.4162,0.00963,0.00314,-0.0005,0.0365,1.0000 4.000,0.4410,0.01016,0.00376,0.0001,0.0318,1.0000 4.250,0.4661,0.01065,0.00432,0.0007,0.0290,1.0000 4.500,0.4899,0.01147,0.00517,0.0012,0.0220,1.0000 4.750,0.5176,0.01124,0.00491,0.0012,0.0162,1.0000 5.000,0.5411,0.01237,0.00618,0.0021,0.0101,1.0000 5.250,0.5658,0.01320,0.00710,0.0027,0.0080,1.0000 5.500,0.5893,0.01451,0.00855,0.0036,0.0071,1.0000 5.750,0.6122,0.01643,0.01070,0.0047,0.0069,1.0000 6.000,0.6352,0.01878,0.01338,0.0058,0.0070,1.0000 6.250,0.6515,0.02639,0.02196,0.0087,0.0091,1.0000 6.500,0.6465,0.02006,0.01635,0.0104,0.0136,1.0000 6.750,0.6591,0.02490,0.02162,0.0116,0.0140,1.0000 7.000,0.6693,0.02927,0.02627,0.0122,0.0138,1.0000 7.250,0.6762,0.03381,0.03104,0.0125,0.0135,1.0000 7.500,0.6786,0.03883,0.03627,0.0127,0.0133,1.0000 7.750,0.6743,0.04435,0.04198,0.0126,0.0130,1.0000 8.000,0.6646,0.04986,0.04765,0.0122,0.0129,1.0000 8.250,0.6499,0.05431,0.05222,0.0120,0.0128,1.0000 8.500,0.6321,0.05881,0.05681,0.0098,0.0129,1.0000 8.750,0.6172,0.06716,0.06523,0.0026,0.0132,1.0000 9.000,0.6067,0.07484,0.07289,-0.0023,0.0133,1.0000 9.250,0.5992,0.08136,0.07940,-0.0056,0.0133,1.0000