Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-eh1070-il-100000 Airfoil,eh1070-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,41.4784 Max Cl/Cd alpha,5 Url,http://airfoiltools.com/polar/csv?polar=xf-eh1070-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.6028,0.09476,0.09022,0.0068,1.0000,0.0848 -8.000,-0.6175,0.09086,0.08640,-0.0003,1.0000,0.0860 -7.750,-0.6320,0.08730,0.08270,-0.0078,1.0000,0.0868 -7.500,-0.6064,0.08181,0.07740,-0.0008,1.0000,0.0909 -7.250,-0.6023,0.07787,0.07345,-0.0027,1.0000,0.0953 -7.000,-0.6167,0.07505,0.07014,-0.0119,1.0000,0.1002 -6.750,-0.5963,0.06877,0.06424,-0.0083,1.0000,0.1038 -6.500,-0.5963,0.06636,0.06130,-0.0129,1.0000,0.1138 -6.250,-0.5786,0.06073,0.05602,-0.0107,1.0000,0.1176 -6.000,-0.5690,0.05694,0.05199,-0.0123,1.0000,0.1290 -5.750,-0.5562,0.05357,0.04844,-0.0127,1.0000,0.1419 -5.500,-0.5415,0.05009,0.04500,-0.0119,1.0000,0.1571 -5.250,-0.5280,0.04730,0.04207,-0.0113,1.0000,0.1833 -4.750,-0.4668,0.03319,0.02599,-0.0116,1.0000,0.0709 -4.500,-0.4413,0.02902,0.02101,-0.0099,1.0000,0.0586 -4.250,-0.4169,0.02573,0.01731,-0.0087,1.0000,0.0556 -4.000,-0.3909,0.02306,0.01420,-0.0075,1.0000,0.0542 -3.750,-0.3644,0.02092,0.01175,-0.0064,1.0000,0.0552 -3.500,-0.3381,0.01938,0.00994,-0.0053,1.0000,0.0612 -3.250,-0.3140,0.01770,0.00833,-0.0043,1.0000,0.0713 -3.000,-0.2913,0.01609,0.00679,-0.0027,1.0000,0.0863 -2.750,-0.2734,0.01396,0.00536,-0.0008,1.0000,0.1746 -2.500,-0.1819,0.01164,0.00560,-0.0072,1.0000,0.9750 -2.250,-0.1089,0.01136,0.00479,-0.0164,1.0000,1.0000 -2.000,-0.0894,0.01114,0.00441,-0.0155,1.0000,1.0000 -1.750,-0.0699,0.01097,0.00406,-0.0144,1.0000,1.0000 -1.500,-0.0506,0.01082,0.00380,-0.0133,1.0000,1.0000 -1.250,-0.0319,0.01071,0.00359,-0.0121,1.0000,1.0000 -1.000,-0.0140,0.01063,0.00345,-0.0107,1.0000,1.0000 -0.750,0.0024,0.01058,0.00336,-0.0090,1.0000,1.0000 -0.500,0.0165,0.01058,0.00333,-0.0069,1.0000,1.0000 -0.250,0.0271,0.01065,0.00336,-0.0044,1.0000,1.0000 0.000,0.0326,0.01084,0.00353,-0.0013,1.0000,1.0000 0.250,0.0343,0.01117,0.00383,0.0021,1.0000,1.0000 0.500,0.1026,0.01137,0.00403,-0.0067,0.9804,1.0000 0.750,0.1699,0.01140,0.00412,-0.0150,0.9594,1.0000 1.000,0.2292,0.01134,0.00411,-0.0211,0.9325,1.0000 1.250,0.2748,0.01130,0.00409,-0.0241,0.9007,1.0000 1.500,0.3025,0.01138,0.00414,-0.0234,0.8645,1.0000 1.750,0.3251,0.01152,0.00427,-0.0216,0.8317,1.0000 2.000,0.3455,0.01171,0.00441,-0.0194,0.7993,1.0000 2.250,0.3660,0.01192,0.00456,-0.0174,0.7693,1.0000 2.500,0.3870,0.01216,0.00474,-0.0154,0.7406,1.0000 2.750,0.4084,0.01241,0.00494,-0.0136,0.7125,1.0000 3.000,0.4304,0.01268,0.00524,-0.0120,0.6850,1.0000 3.250,0.4529,0.01297,0.00551,-0.0106,0.6579,1.0000 3.500,0.4758,0.01326,0.00581,-0.0092,0.6308,1.0000 3.750,0.4987,0.01357,0.00612,-0.0079,0.6031,1.0000 4.000,0.5218,0.01387,0.00645,-0.0065,0.5748,1.0000 4.250,0.5450,0.01417,0.00682,-0.0053,0.5442,1.0000 4.500,0.5679,0.01444,0.00722,-0.0039,0.5107,1.0000 4.750,0.5866,0.01433,0.00695,-0.0015,0.4406,1.0000 5.000,0.6060,0.01461,0.00701,0.0003,0.3353,1.0000 5.250,0.6149,0.01824,0.00883,0.0026,0.0724,1.0000 5.500,0.6346,0.01995,0.01059,0.0042,0.0587,1.0000 5.750,0.6544,0.02169,0.01230,0.0056,0.0496,1.0000 6.000,0.6769,0.02342,0.01408,0.0069,0.0452,1.0000 6.250,0.7005,0.02565,0.01637,0.0080,0.0432,1.0000 6.500,0.7251,0.02827,0.01927,0.0091,0.0426,1.0000 6.750,0.7494,0.03113,0.02254,0.0105,0.0434,1.0000 7.000,0.7703,0.03476,0.02689,0.0121,0.0460,1.0000 7.250,0.7876,0.03857,0.03127,0.0135,0.0473,1.0000 7.500,0.8015,0.04243,0.03565,0.0146,0.0473,1.0000 7.750,0.8122,0.04705,0.04071,0.0155,0.0496,1.0000 8.000,0.8155,0.05353,0.04794,0.0164,0.0609,1.0000 10.000,0.7425,0.11089,0.10624,-0.0104,0.1296,1.0000 10.250,0.7083,0.11567,0.11079,-0.0196,0.1254,1.0000 10.500,0.6386,0.11525,0.11079,-0.0094,0.1298,1.0000