Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-hq09-il-100000 Airfoil,hq09-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,36.8272 Max Cl/Cd alpha,4 Url,http://airfoiltools.com/polar/csv?polar=xf-hq09-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.750,-0.5705,0.10293,0.09855,0.0068,1.0000,0.1215 -9.500,-0.5902,0.09764,0.09333,0.0021,1.0000,0.1224 -9.250,-0.6040,0.09160,0.08736,-0.0015,1.0000,0.1235 -9.000,-0.5702,0.08900,0.08471,0.0044,1.0000,0.1401 -8.750,-0.5786,0.08439,0.08013,0.0022,1.0000,0.1473 -8.500,-0.6119,0.07837,0.07422,-0.0044,1.0000,0.1489 -8.250,-0.5885,0.07463,0.07042,-0.0004,1.0000,0.1594 -7.250,-0.7210,0.04714,0.04064,-0.0147,1.0000,0.0562 -7.000,-0.7085,0.04240,0.03552,-0.0138,1.0000,0.0558 -6.750,-0.6954,0.03848,0.03094,-0.0125,1.0000,0.0576 -6.500,-0.6772,0.03427,0.02624,-0.0113,1.0000,0.0578 -6.250,-0.6566,0.03053,0.02220,-0.0104,1.0000,0.0599 -6.000,-0.6340,0.02857,0.01997,-0.0095,1.0000,0.0671 -5.750,-0.6090,0.02609,0.01695,-0.0083,1.0000,0.0690 -5.500,-0.5837,0.02334,0.01401,-0.0075,1.0000,0.0726 -5.250,-0.5590,0.02206,0.01256,-0.0068,1.0000,0.0819 -5.000,-0.5346,0.02007,0.01067,-0.0059,1.0000,0.0893 -4.750,-0.5115,0.01849,0.00913,-0.0048,1.0000,0.0998 -4.500,-0.4905,0.01707,0.00784,-0.0034,1.0000,0.1222 -4.250,-0.4735,0.01517,0.00664,-0.0018,1.0000,0.1995 -4.000,-0.4668,0.01267,0.00596,0.0016,1.0000,0.4994 -3.750,-0.4522,0.01235,0.00616,0.0055,1.0000,0.6488 -3.500,-0.4353,0.01237,0.00622,0.0090,1.0000,0.7185 -3.250,-0.4190,0.01246,0.00633,0.0127,1.0000,0.7671 -3.000,-0.4033,0.01253,0.00637,0.0165,1.0000,0.8057 -2.750,-0.3886,0.01263,0.00646,0.0207,1.0000,0.8421 -2.500,-0.3702,0.01280,0.00659,0.0245,1.0000,0.8776 -2.250,-0.3390,0.01295,0.00657,0.0251,1.0000,0.9048 -2.000,-0.2994,0.01299,0.00644,0.0232,1.0000,0.9240 -1.750,-0.2539,0.01302,0.00630,0.0198,1.0000,0.9409 -1.500,-0.1933,0.01307,0.00614,0.0135,1.0000,0.9548 -1.250,-0.1138,0.01306,0.00593,0.0036,1.0000,0.9706 -1.000,-0.0506,0.01280,0.00557,-0.0038,1.0000,0.9848 -0.750,0.0025,0.01245,0.00517,-0.0097,1.0000,0.9964 -0.500,0.0257,0.01222,0.00495,-0.0104,1.0000,1.0000 -0.250,0.0238,0.01213,0.00493,-0.0068,1.0000,1.0000 0.000,0.0000,0.01215,0.00498,0.0000,1.0000,1.0000 0.250,-0.0238,0.01213,0.00493,0.0068,1.0000,1.0000 0.500,-0.0257,0.01221,0.00495,0.0104,1.0000,1.0000 0.750,-0.0025,0.01245,0.00516,0.0097,0.9965,1.0000 1.000,0.0506,0.01280,0.00557,0.0038,0.9848,1.0000 1.250,0.1138,0.01306,0.00593,-0.0037,0.9706,1.0000 1.500,0.1934,0.01307,0.00613,-0.0135,0.9548,1.0000 1.750,0.2539,0.01301,0.00629,-0.0198,0.9409,1.0000 2.000,0.2993,0.01299,0.00644,-0.0232,0.9240,1.0000 2.250,0.3389,0.01295,0.00656,-0.0251,0.9048,1.0000 2.500,0.3699,0.01280,0.00659,-0.0244,0.8776,1.0000 2.750,0.3883,0.01263,0.00646,-0.0206,0.8421,1.0000 3.000,0.4030,0.01253,0.00637,-0.0164,0.8058,1.0000 3.250,0.4187,0.01246,0.00633,-0.0127,0.7672,1.0000 3.500,0.4351,0.01237,0.00622,-0.0089,0.7190,1.0000 3.750,0.4519,0.01235,0.00616,-0.0054,0.6491,1.0000 4.000,0.4666,0.01267,0.00596,-0.0016,0.5001,1.0000 4.250,0.4734,0.01517,0.00664,0.0018,0.1996,1.0000 4.500,0.4904,0.01708,0.00784,0.0035,0.1224,1.0000 4.750,0.5115,0.01848,0.00912,0.0048,0.0999,1.0000 5.000,0.5346,0.02007,0.01067,0.0059,0.0894,1.0000 5.250,0.5590,0.02206,0.01255,0.0068,0.0820,1.0000 5.500,0.5837,0.02334,0.01401,0.0075,0.0726,1.0000 5.750,0.6090,0.02609,0.01696,0.0083,0.0690,1.0000 6.000,0.6341,0.02858,0.01997,0.0095,0.0670,1.0000 6.250,0.6568,0.03055,0.02223,0.0104,0.0600,1.0000 6.500,0.6773,0.03430,0.02626,0.0112,0.0578,1.0000 6.750,0.6961,0.03824,0.03073,0.0125,0.0578,1.0000 7.000,0.7087,0.04257,0.03565,0.0137,0.0560,1.0000 7.250,0.7212,0.04720,0.04071,0.0147,0.0562,1.0000 8.500,0.7293,0.08324,0.07868,0.0103,0.1227,1.0000 8.750,0.6939,0.08757,0.08312,0.0044,0.1219,1.0000 9.000,0.6646,0.09368,0.08910,-0.0047,0.1195,1.0000