Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-hq07-il-50000-n5 Airfoil,hq07-il Reynolds number,50000 Ncrit,5 Mach,0 Max Cl/Cd,24.7062 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-hq07-il-50000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.6623,0.09326,0.08662,0.0038,1.0000,0.0358 -8.750,-0.6675,0.08692,0.08034,-0.0013,1.0000,0.0348 -8.500,-0.6795,0.08031,0.07375,-0.0070,1.0000,0.0335 -8.000,-0.6946,0.07056,0.06359,-0.0120,1.0000,0.0316 -7.750,-0.6947,0.06591,0.05876,-0.0129,1.0000,0.0315 -7.500,-0.6922,0.06128,0.05390,-0.0134,1.0000,0.0314 -7.250,-0.6869,0.05672,0.04903,-0.0136,1.0000,0.0313 -7.000,-0.6786,0.05225,0.04416,-0.0135,1.0000,0.0313 -6.750,-0.6670,0.04801,0.03943,-0.0131,1.0000,0.0315 -6.500,-0.6529,0.04377,0.03470,-0.0125,1.0000,0.0320 -6.250,-0.6372,0.03960,0.03018,-0.0120,1.0000,0.0335 -6.000,-0.6178,0.03653,0.02678,-0.0113,1.0000,0.0368 -5.750,-0.5968,0.03384,0.02349,-0.0105,1.0000,0.0459 -5.500,-0.5730,0.03091,0.02027,-0.0096,1.0000,0.0507 -5.250,-0.5464,0.02831,0.01720,-0.0084,1.0000,0.0554 -5.000,-0.5217,0.02617,0.01494,-0.0073,1.0000,0.0615 -4.750,-0.4982,0.02471,0.01335,-0.0065,1.0000,0.0771 -4.500,-0.4749,0.02309,0.01159,-0.0053,1.0000,0.0883 -4.250,-0.4523,0.02153,0.00994,-0.0043,1.0000,0.1078 -4.000,-0.4320,0.01955,0.00840,-0.0038,1.0000,0.1840 -3.750,-0.4202,0.01725,0.00758,-0.0016,1.0000,0.4284 -3.500,-0.4081,0.01651,0.00774,0.0033,1.0000,0.6441 -3.250,-0.3928,0.01646,0.00785,0.0082,1.0000,0.7557 -3.000,-0.3708,0.01656,0.00789,0.0121,1.0000,0.8313 -2.750,-0.3383,0.01649,0.00752,0.0125,1.0000,0.8688 -2.500,-0.3008,0.01635,0.00707,0.0112,1.0000,0.8960 -2.250,-0.2524,0.01629,0.00668,0.0079,1.0000,0.9291 -2.000,-0.1902,0.01615,0.00603,0.0014,1.0000,0.9573 -1.750,-0.1424,0.01585,0.00550,-0.0031,1.0000,0.9747 -1.500,-0.0986,0.01552,0.00501,-0.0071,1.0000,0.9906 -1.250,-0.0671,0.01524,0.00463,-0.0089,1.0000,1.0000 -1.000,-0.0518,0.01502,0.00440,-0.0076,1.0000,1.0000 -0.750,-0.0374,0.01484,0.00419,-0.0060,1.0000,1.0000 -0.500,-0.0240,0.01471,0.00405,-0.0042,1.0000,1.0000 -0.250,-0.0116,0.01463,0.00397,-0.0022,1.0000,1.0000 0.000,0.0000,0.01460,0.00394,0.0000,1.0000,1.0000 0.250,0.0116,0.01463,0.00396,0.0022,1.0000,1.0000 0.500,0.0240,0.01471,0.00405,0.0042,1.0000,1.0000 0.750,0.0375,0.01484,0.00418,0.0060,1.0000,1.0000 1.000,0.0519,0.01502,0.00439,0.0076,1.0000,1.0000 1.250,0.0673,0.01523,0.00463,0.0089,1.0000,1.0000 1.500,0.0987,0.01552,0.00500,0.0071,0.9907,1.0000 1.750,0.1424,0.01584,0.00549,0.0031,0.9747,1.0000 2.000,0.1903,0.01614,0.00602,-0.0014,0.9574,1.0000 2.250,0.2525,0.01629,0.00667,-0.0079,0.9291,1.0000 2.500,0.3009,0.01635,0.00706,-0.0112,0.8961,1.0000 2.750,0.3383,0.01648,0.00752,-0.0125,0.8688,1.0000 3.000,0.3707,0.01655,0.00789,-0.0121,0.8313,1.0000 3.250,0.3927,0.01645,0.00785,-0.0082,0.7558,1.0000 3.500,0.4079,0.01651,0.00774,-0.0033,0.6432,1.0000 3.750,0.4201,0.01725,0.00757,0.0016,0.4287,1.0000 4.000,0.4320,0.01956,0.00840,0.0038,0.1838,1.0000 4.250,0.4524,0.02153,0.00994,0.0043,0.1078,1.0000 4.500,0.4750,0.02309,0.01159,0.0053,0.0881,1.0000 4.750,0.4984,0.02472,0.01336,0.0065,0.0769,1.0000 5.000,0.5219,0.02617,0.01494,0.0073,0.0615,1.0000 5.250,0.5466,0.02832,0.01720,0.0084,0.0554,1.0000 5.500,0.5733,0.03092,0.02028,0.0096,0.0507,1.0000 5.750,0.5970,0.03386,0.02350,0.0105,0.0457,1.0000 6.000,0.6182,0.03653,0.02678,0.0112,0.0366,1.0000 6.250,0.6376,0.03965,0.03023,0.0119,0.0334,1.0000 6.500,0.6535,0.04377,0.03471,0.0124,0.0321,1.0000 6.750,0.6676,0.04806,0.03948,0.0130,0.0315,1.0000 7.000,0.6791,0.05236,0.04428,0.0134,0.0313,1.0000 7.250,0.6876,0.05679,0.04911,0.0134,0.0313,1.0000 7.500,0.6927,0.06142,0.05405,0.0132,0.0313,1.0000 7.750,0.6956,0.06597,0.05883,0.0127,0.0315,1.0000 8.000,0.6959,0.07061,0.06363,0.0118,0.0317,1.0000 8.500,0.6805,0.08045,0.07390,0.0068,0.0335,1.0000 8.750,0.6685,0.08706,0.08048,0.0011,0.0347,1.0000 9.000,0.6634,0.09340,0.08676,-0.0041,0.0358,1.0000