Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-eh0009-il-50000 Airfoil,eh0009-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,26.6619 Max Cl/Cd alpha,4.75 Url,http://airfoiltools.com/polar/csv?polar=xf-eh0009-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.7324,0.08076,0.07436,-0.0161,1.0000,0.1176 -8.750,-0.7284,0.07567,0.06914,-0.0165,1.0000,0.1153 -8.500,-0.7605,0.06814,0.06130,-0.0194,1.0000,0.1034 -8.250,-0.7599,0.06316,0.05614,-0.0193,1.0000,0.1027 -8.000,-0.7599,0.05833,0.05101,-0.0190,1.0000,0.1022 -7.750,-0.7584,0.05363,0.04588,-0.0182,1.0000,0.1024 -7.500,-0.7525,0.04916,0.04080,-0.0172,1.0000,0.1027 -7.250,-0.7417,0.04484,0.03593,-0.0158,1.0000,0.1029 -7.000,-0.7274,0.04087,0.03129,-0.0143,1.0000,0.1038 -6.750,-0.7069,0.03731,0.02773,-0.0133,1.0000,0.1096 -6.500,-0.6883,0.03455,0.02459,-0.0120,1.0000,0.1208 -6.250,-0.6658,0.03165,0.02129,-0.0106,1.0000,0.1318 -6.000,-0.6425,0.02913,0.01881,-0.0094,1.0000,0.1510 -5.750,-0.6210,0.02690,0.01654,-0.0078,1.0000,0.1847 -5.500,-0.6018,0.02467,0.01474,-0.0059,1.0000,0.2404 -5.250,-0.5877,0.02298,0.01363,-0.0032,1.0000,0.3233 -5.000,-0.5739,0.02172,0.01293,0.0002,1.0000,0.4133 -4.750,-0.5592,0.02097,0.01251,0.0040,1.0000,0.4964 -4.500,-0.5436,0.02053,0.01232,0.0081,1.0000,0.5694 -4.250,-0.5265,0.02036,0.01232,0.0125,1.0000,0.6317 -4.000,-0.5089,0.02032,0.01234,0.0169,1.0000,0.6880 -3.750,-0.4895,0.02041,0.01241,0.0213,1.0000,0.7388 -3.500,-0.4664,0.02058,0.01247,0.0251,1.0000,0.7871 -3.250,-0.4288,0.02095,0.01256,0.0265,1.0000,0.8335 -3.000,-0.3600,0.02149,0.01264,0.0219,1.0000,0.8796 -2.750,-0.2623,0.02157,0.01210,0.0101,1.0000,0.9223 -2.500,-0.1727,0.02085,0.01096,-0.0020,1.0000,0.9601 -2.250,-0.0851,0.01956,0.00931,-0.0152,1.0000,0.9947 -2.000,-0.0606,0.01875,0.00841,-0.0170,1.0000,1.0000 -1.750,-0.0492,0.01818,0.00781,-0.0162,1.0000,1.0000 -1.500,-0.0382,0.01770,0.00731,-0.0150,1.0000,1.0000 -1.250,-0.0279,0.01729,0.00690,-0.0135,1.0000,1.0000 -1.000,-0.0188,0.01697,0.00659,-0.0116,1.0000,1.0000 -0.750,-0.0115,0.01671,0.00634,-0.0093,1.0000,1.0000 -0.500,-0.0062,0.01653,0.00618,-0.0065,1.0000,1.0000 -0.250,-0.0024,0.01642,0.00609,-0.0034,1.0000,1.0000 0.000,0.0000,0.01638,0.00605,0.0000,1.0000,1.0000 0.250,0.0025,0.01642,0.00608,0.0034,1.0000,1.0000 0.500,0.0062,0.01653,0.00618,0.0065,1.0000,1.0000 0.750,0.0115,0.01671,0.00634,0.0093,1.0000,1.0000 1.000,0.0189,0.01697,0.00658,0.0116,1.0000,1.0000 1.250,0.0280,0.01729,0.00690,0.0135,1.0000,1.0000 1.500,0.0383,0.01769,0.00731,0.0150,1.0000,1.0000 1.750,0.0493,0.01817,0.00780,0.0162,1.0000,1.0000 2.000,0.0607,0.01874,0.00840,0.0170,1.0000,1.0000 2.250,0.0849,0.01955,0.00929,0.0152,0.9948,1.0000 2.500,0.1728,0.02084,0.01095,0.0020,0.9602,1.0000 2.750,0.2623,0.02156,0.01210,-0.0101,0.9224,1.0000 3.000,0.3601,0.02148,0.01263,-0.0219,0.8796,1.0000 3.250,0.4286,0.02095,0.01255,-0.0265,0.8337,1.0000 3.500,0.4663,0.02057,0.01246,-0.0251,0.7873,1.0000 3.750,0.4894,0.02041,0.01241,-0.0213,0.7389,1.0000 4.000,0.5088,0.02032,0.01234,-0.0169,0.6881,1.0000 4.250,0.5264,0.02036,0.01232,-0.0124,0.6319,1.0000 4.500,0.5434,0.02053,0.01232,-0.0081,0.5695,1.0000 4.750,0.5591,0.02097,0.01251,-0.0040,0.4966,1.0000 5.000,0.5738,0.02172,0.01293,-0.0002,0.4135,1.0000 5.250,0.5876,0.02298,0.01363,0.0032,0.3232,1.0000 5.500,0.6018,0.02467,0.01474,0.0059,0.2404,1.0000 5.750,0.6210,0.02690,0.01654,0.0078,0.1847,1.0000 6.000,0.6424,0.02912,0.01880,0.0094,0.1508,1.0000 6.250,0.6658,0.03164,0.02128,0.0106,0.1319,1.0000 6.500,0.6883,0.03453,0.02456,0.0120,0.1207,1.0000 6.750,0.7069,0.03730,0.02771,0.0133,0.1094,1.0000 7.000,0.7274,0.04089,0.03130,0.0143,0.1038,1.0000 7.250,0.7417,0.04484,0.03593,0.0158,0.1029,1.0000 7.500,0.7526,0.04916,0.04080,0.0171,0.1026,1.0000 7.750,0.7584,0.05366,0.04592,0.0182,0.1024,1.0000 8.000,0.7603,0.05834,0.05102,0.0189,0.1023,1.0000 8.250,0.7595,0.06320,0.05620,0.0192,0.1026,1.0000 8.500,0.7609,0.06819,0.06134,0.0193,0.1034,1.0000 8.750,0.7283,0.07572,0.06919,0.0163,0.1153,1.0000 9.000,0.7332,0.08083,0.07442,0.0160,0.1176,1.0000 9.250,0.5804,0.08585,0.07963,0.0060,0.1411,1.0000