Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-eh1090-il-500000 Airfoil,eh1090-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,74.3908 Max Cl/Cd alpha,4.75 Url,http://airfoiltools.com/polar/csv?polar=xf-eh1090-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.750,-0.6529,0.05092,0.04814,-0.0191,1.0000,0.0213 -7.500,-0.6512,0.04674,0.04368,-0.0180,1.0000,0.0213 -7.250,-0.6814,0.03090,0.02679,-0.0137,1.0000,0.0141 -7.000,-0.6703,0.02656,0.02212,-0.0119,1.0000,0.0131 -6.750,-0.6538,0.02385,0.01904,-0.0103,1.0000,0.0132 -6.500,-0.6342,0.02192,0.01683,-0.0089,1.0000,0.0134 -6.250,-0.6139,0.02025,0.01484,-0.0076,1.0000,0.0141 -6.000,-0.5932,0.01827,0.01262,-0.0063,1.0000,0.0141 -5.750,-0.5722,0.01647,0.01063,-0.0049,1.0000,0.0141 -5.500,-0.5524,0.01467,0.00866,-0.0033,1.0000,0.0144 -5.250,-0.5337,0.01317,0.00703,-0.0015,1.0000,0.0153 -5.000,-0.5132,0.01236,0.00616,-0.0001,1.0000,0.0165 -4.750,-0.4922,0.01177,0.00554,0.0013,1.0000,0.0179 -4.500,-0.4716,0.01124,0.00495,0.0027,1.0000,0.0195 -4.250,-0.4498,0.01089,0.00453,0.0039,0.9997,0.0213 -4.000,-0.4120,0.00993,0.00359,0.0017,0.9943,0.0372 -3.750,-0.3752,0.00934,0.00317,-0.0004,0.9874,0.0731 -3.500,-0.3367,0.00892,0.00289,-0.0029,0.9810,0.1100 -3.250,-0.3017,0.00840,0.00262,-0.0047,0.9703,0.1702 -3.000,-0.2690,0.00781,0.00237,-0.0061,0.9564,0.2590 -2.750,-0.2405,0.00713,0.00213,-0.0065,0.9376,0.3777 -2.500,-0.2172,0.00644,0.00194,-0.0056,0.9151,0.5194 -2.250,-0.1960,0.00597,0.00183,-0.0040,0.8907,0.6352 -2.000,-0.1736,0.00574,0.00175,-0.0025,0.8667,0.7093 -1.750,-0.1500,0.00563,0.00170,-0.0012,0.8431,0.7599 -1.500,-0.1263,0.00557,0.00168,0.0002,0.8194,0.8054 -1.250,-0.1016,0.00558,0.00166,0.0013,0.7965,0.8351 -1.000,-0.0765,0.00562,0.00162,0.0022,0.7744,0.8586 -0.750,-0.0509,0.00566,0.00160,0.0030,0.7522,0.8761 -0.500,-0.0254,0.00573,0.00160,0.0039,0.7311,0.8943 -0.250,-0.0003,0.00581,0.00161,0.0049,0.7101,0.9137 0.000,0.0259,0.00592,0.00164,0.0056,0.6901,0.9297 0.250,0.0536,0.00603,0.00168,0.0060,0.6699,0.9432 0.500,0.0831,0.00618,0.00173,0.0060,0.6505,0.9556 0.750,0.1204,0.00634,0.00181,0.0043,0.6306,0.9635 1.000,0.1566,0.00649,0.00186,0.0027,0.6109,0.9707 1.250,0.1979,0.00662,0.00189,-0.0002,0.5913,0.9741 1.500,0.2353,0.00673,0.00192,-0.0022,0.5709,0.9786 1.750,0.2696,0.00684,0.00196,-0.0037,0.5522,0.9832 2.000,0.3077,0.00692,0.00197,-0.0060,0.5325,0.9858 2.250,0.3447,0.00701,0.00199,-0.0080,0.5134,0.9893 2.500,0.3803,0.00712,0.00205,-0.0098,0.4946,0.9934 2.750,0.4174,0.00720,0.00207,-0.0119,0.4729,0.9964 3.000,0.4541,0.00730,0.00211,-0.0140,0.4503,0.9995 3.250,0.4795,0.00739,0.00215,-0.0137,0.4324,1.0000 3.500,0.5025,0.00748,0.00223,-0.0129,0.4164,1.0000 3.750,0.5254,0.00760,0.00232,-0.0120,0.4009,1.0000 4.000,0.5483,0.00773,0.00242,-0.0111,0.3836,1.0000 4.250,0.5713,0.00788,0.00254,-0.0103,0.3636,1.0000 4.500,0.5940,0.00807,0.00268,-0.0094,0.3441,1.0000 4.750,0.6167,0.00829,0.00285,-0.0085,0.3168,1.0000 5.000,0.6386,0.00863,0.00303,-0.0075,0.2730,1.0000 5.250,0.6605,0.00901,0.00325,-0.0066,0.2344,1.0000 5.500,0.6825,0.00940,0.00352,-0.0057,0.1979,1.0000 5.750,0.7038,0.00991,0.00385,-0.0047,0.1551,1.0000 6.000,0.7236,0.01068,0.00435,-0.0036,0.0979,1.0000 6.250,0.7395,0.01206,0.00531,-0.0018,0.0260,1.0000 6.500,0.7592,0.01296,0.00627,-0.0004,0.0185,1.0000 6.750,0.7813,0.01349,0.00688,0.0006,0.0170,1.0000 7.000,0.8026,0.01415,0.00764,0.0017,0.0156,1.0000 7.250,0.8232,0.01492,0.00850,0.0029,0.0143,1.0000 7.500,0.8419,0.01596,0.00961,0.0042,0.0129,1.0000 7.750,0.8550,0.01788,0.01169,0.0063,0.0116,1.0000 8.000,0.8765,0.01858,0.01251,0.0073,0.0110,1.0000 8.250,0.8960,0.01964,0.01368,0.0084,0.0104,1.0000 8.500,0.9144,0.02095,0.01513,0.0097,0.0100,1.0000 8.750,0.9322,0.02245,0.01677,0.0111,0.0095,1.0000 9.000,0.9493,0.02407,0.01854,0.0124,0.0091,1.0000 9.250,0.9648,0.02611,0.02079,0.0138,0.0089,1.0000 9.500,0.9776,0.02869,0.02364,0.0155,0.0090,1.0000