Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-hq308-il-1000000 Airfoil,hq308-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,135.389 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-hq308-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.3668,0.08788,0.08631,-0.0322,1.0000,0.0056 -8.000,-0.3682,0.08500,0.08346,-0.0323,1.0000,0.0056 -7.750,-0.3744,0.08266,0.08117,-0.0312,1.0000,0.0056 -7.500,-0.3717,0.07917,0.07770,-0.0334,0.9986,0.0056 -7.250,-0.3515,0.07357,0.07211,-0.0417,0.9939,0.0056 -7.000,-0.3288,0.06762,0.06615,-0.0513,0.9887,0.0057 -6.750,-0.2989,0.06020,0.05869,-0.0646,0.9845,0.0057 -6.500,-0.2669,0.05305,0.05142,-0.0756,0.9821,0.0057 -6.250,-0.2403,0.04707,0.04530,-0.0826,0.9755,0.0057 -6.000,-0.2144,0.03644,0.03434,-0.0920,0.9686,0.0060 -5.750,-0.1945,0.03191,0.02957,-0.0940,0.9583,0.0063 -5.500,-0.1723,0.02901,0.02646,-0.0949,0.9499,0.0066 -5.250,-0.1494,0.02633,0.02357,-0.0954,0.9422,0.0070 -5.000,-0.1264,0.02381,0.02082,-0.0953,0.9336,0.0079 -4.750,-0.1010,0.02139,0.01815,-0.0949,0.9265,0.0092 -3.500,0.0288,0.01062,0.00587,-0.0928,0.8920,0.0117 -3.250,0.0561,0.00985,0.00499,-0.0923,0.8857,0.0099 -3.000,0.0825,0.00862,0.00360,-0.0918,0.8786,0.0093 -2.750,0.1094,0.00789,0.00272,-0.0915,0.8714,0.0091 -2.500,0.1366,0.00740,0.00210,-0.0912,0.8629,0.0094 -2.250,0.1642,0.00711,0.00171,-0.0910,0.8544,0.0104 -2.000,0.1920,0.00682,0.00130,-0.0908,0.8472,0.0160 -1.750,0.2197,0.00653,0.00115,-0.0908,0.8396,0.0602 -1.500,0.2469,0.00615,0.00103,-0.0908,0.8316,0.1611 -1.250,0.2729,0.00536,0.00091,-0.0910,0.8216,0.4114 -1.000,0.2992,0.00493,0.00091,-0.0909,0.8110,0.5750 -0.750,0.3264,0.00484,0.00090,-0.0907,0.8018,0.6289 -0.500,0.3538,0.00481,0.00088,-0.0906,0.7931,0.6571 -0.250,0.3812,0.00478,0.00089,-0.0904,0.7835,0.6863 0.000,0.4082,0.00475,0.00091,-0.0901,0.7726,0.7237 0.250,0.4345,0.00472,0.00094,-0.0897,0.7588,0.7636 0.500,0.4614,0.00473,0.00094,-0.0894,0.7448,0.7816 0.750,0.4886,0.00475,0.00095,-0.0892,0.7324,0.7948 1.000,0.5156,0.00477,0.00097,-0.0890,0.7194,0.8092 1.250,0.5424,0.00479,0.00099,-0.0887,0.7060,0.8262 1.500,0.5687,0.00481,0.00102,-0.0884,0.6903,0.8473 1.750,0.5936,0.00479,0.00106,-0.0876,0.6734,0.8816 2.000,0.6248,0.00470,0.00107,-0.0883,0.6542,1.0000 2.250,0.6516,0.00484,0.00112,-0.0881,0.6324,1.0000 2.500,0.6783,0.00501,0.00119,-0.0879,0.6062,1.0000 2.750,0.7044,0.00522,0.00130,-0.0876,0.5747,1.0000 3.000,0.7300,0.00548,0.00141,-0.0873,0.5371,1.0000 3.250,0.7541,0.00590,0.00158,-0.0867,0.4760,1.0000 3.500,0.7776,0.00641,0.00179,-0.0860,0.4101,1.0000 3.750,0.8024,0.00680,0.00198,-0.0856,0.3645,1.0000 4.000,0.8264,0.00728,0.00223,-0.0851,0.3098,1.0000 4.250,0.8501,0.00779,0.00249,-0.0846,0.2566,1.0000 4.500,0.8738,0.00831,0.00276,-0.0841,0.2050,1.0000 4.750,0.8982,0.00874,0.00302,-0.0836,0.1709,1.0000 5.000,0.9227,0.00915,0.00330,-0.0832,0.1396,1.0000 5.250,0.9463,0.00967,0.00364,-0.0827,0.1022,1.0000 5.500,0.9680,0.01043,0.00410,-0.0819,0.0526,1.0000 5.750,0.9904,0.01109,0.00458,-0.0811,0.0220,1.0000 6.000,1.0134,0.01172,0.00508,-0.0804,0.0060,1.0000 6.250,1.0378,0.01217,0.00560,-0.0797,0.0039,1.0000 6.500,1.0621,0.01262,0.00614,-0.0791,0.0037,1.0000 6.750,1.0858,0.01314,0.00675,-0.0784,0.0035,1.0000 7.000,1.1089,0.01374,0.00748,-0.0776,0.0035,1.0000 7.250,1.1309,0.01446,0.00832,-0.0766,0.0035,1.0000 7.500,1.1515,0.01535,0.00935,-0.0753,0.0035,1.0000 7.750,1.1708,0.01637,0.01051,-0.0739,0.0036,1.0000 8.000,1.1878,0.01767,0.01196,-0.0721,0.0037,1.0000 8.250,1.2017,0.01947,0.01395,-0.0698,0.0038,1.0000 8.500,1.2158,0.02144,0.01607,-0.0677,0.0040,1.0000 8.750,1.2336,0.02278,0.01753,-0.0662,0.0041,1.0000 9.000,1.2481,0.02490,0.01984,-0.0643,0.0041,1.0000 9.250,1.2640,0.02660,0.02170,-0.0627,0.0041,1.0000