Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-m22-il-1000000 Airfoil,m22-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,115 Max Cl/Cd alpha,5.5 Url,http://airfoiltools.com/polar/csv?polar=xf-m22-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.750,-0.4583,0.10591,0.10352,0.0353,0.6390,0.0076 -7.500,-0.4529,0.10286,0.10046,0.0335,0.6338,0.0077 -7.000,-0.4356,0.09661,0.09418,0.0287,0.6238,0.0080 -6.750,-0.4232,0.09333,0.09087,0.0258,0.6185,0.0082 -6.500,-0.4093,0.08996,0.08745,0.0229,0.6137,0.0085 -6.250,-0.3940,0.08651,0.08397,0.0198,0.6086,0.0089 -6.000,-0.3765,0.08284,0.08026,0.0166,0.6036,0.0099 -5.750,-0.3512,0.07894,0.07630,0.0116,0.5991,0.0104 -5.500,-0.3282,0.07498,0.07228,0.0076,0.5943,0.0105 -5.250,-0.3053,0.07113,0.06836,0.0043,0.5894,0.0105 -5.000,-0.2913,0.06649,0.06367,0.0026,0.5851,0.0109 -4.750,-0.2703,0.06379,0.06093,0.0008,0.5800,0.0112 -4.500,-0.2470,0.06116,0.05822,-0.0012,0.5748,0.0118 -4.250,-0.2213,0.05829,0.05526,-0.0035,0.5702,0.0133 -4.000,-0.1853,0.05513,0.05198,-0.0068,0.5657,0.0142 -3.750,-0.1553,0.05162,0.04834,-0.0091,0.5612,0.0143 -3.500,-0.1260,0.04806,0.04465,-0.0108,0.5569,0.0144 -3.250,-0.1058,0.04368,0.04020,-0.0119,0.5528,0.0149 -3.000,-0.0817,0.04186,0.03831,-0.0126,0.5480,0.0154 -2.750,-0.0552,0.04008,0.03642,-0.0135,0.5433,0.0167 -2.500,-0.0169,0.03826,0.03443,-0.0145,0.5393,0.0190 -2.250,0.0128,0.03560,0.03163,-0.0150,0.5350,0.0191 -1.750,0.0672,0.02863,0.02430,-0.0158,0.5275,0.0200 -1.500,0.0925,0.02747,0.02308,-0.0162,0.5231,0.0207 -1.250,0.1197,0.02626,0.02177,-0.0165,0.5187,0.0221 -1.000,0.1520,0.02544,0.02079,-0.0164,0.5146,0.0254 -0.750,0.1818,0.02404,0.01927,-0.0164,0.5109,0.0258 -0.500,0.2110,0.02237,0.01745,-0.0162,0.5067,0.0259 -0.250,0.2402,0.02048,0.01536,-0.0160,0.5028,0.0260 1.000,0.3807,0.01348,0.00757,-0.0162,0.4836,0.0311 1.250,0.4094,0.01285,0.00684,-0.0162,0.4796,0.0333 1.500,0.4384,0.01318,0.00711,-0.0163,0.4755,0.0355 1.750,0.4671,0.01254,0.00632,-0.0163,0.4716,0.0357 2.500,0.5518,0.01057,0.00413,-0.0168,0.4592,0.0471 2.750,0.5804,0.01037,0.00391,-0.0169,0.4556,0.0477 3.250,0.6356,0.00910,0.00255,-0.0166,0.4475,0.0341 3.500,0.6634,0.00892,0.00235,-0.0167,0.4433,0.0333 3.750,0.6914,0.00878,0.00222,-0.0168,0.4392,0.0329 4.000,0.7196,0.00872,0.00213,-0.0170,0.4327,0.0331 4.250,0.7478,0.00867,0.00208,-0.0172,0.4250,0.0342 4.500,0.7761,0.00870,0.00208,-0.0175,0.4169,0.0363 4.750,0.8044,0.00872,0.00208,-0.0177,0.4066,0.0394 5.000,0.8327,0.00881,0.00214,-0.0181,0.3919,0.0435 5.250,0.8606,0.00888,0.00231,-0.0185,0.3719,0.1380 5.500,0.8993,0.00782,0.00275,-0.0217,0.3248,0.9952 5.750,0.9578,0.01166,0.00507,-0.0323,0.0186,1.0000 6.000,0.9830,0.01202,0.00550,-0.0321,0.0149,1.0000 6.250,1.0080,0.01238,0.00590,-0.0320,0.0141,1.0000 6.500,1.0328,0.01277,0.00634,-0.0318,0.0133,1.0000 6.750,1.0572,0.01325,0.00687,-0.0316,0.0121,1.0000 7.000,1.0811,0.01379,0.00745,-0.0314,0.0109,1.0000 7.250,1.1040,0.01457,0.00830,-0.0312,0.0101,1.0000 7.500,1.1238,0.01600,0.00989,-0.0310,0.0094,1.0000 7.750,1.1421,0.01728,0.01127,-0.0306,0.0090,1.0000 8.000,1.1631,0.01788,0.01192,-0.0300,0.0086,1.0000 8.250,1.1810,0.01885,0.01296,-0.0293,0.0082,1.0000 8.500,1.1950,0.02014,0.01433,-0.0283,0.0079,1.0000 8.750,1.2070,0.02147,0.01574,-0.0271,0.0076,1.0000 9.000,1.2188,0.02270,0.01702,-0.0261,0.0072,1.0000 9.250,1.2286,0.02425,0.01863,-0.0257,0.0069,1.0000 9.500,1.2294,0.02612,0.02055,-0.0241,0.0068,1.0000 9.750,1.2343,0.02793,0.02243,-0.0228,0.0067,1.0000 10.000,1.2411,0.02965,0.02419,-0.0216,0.0066,1.0000 10.250,1.2496,0.03125,0.02584,-0.0204,0.0065,1.0000 10.500,1.2588,0.03279,0.02742,-0.0192,0.0063,1.0000 10.750,1.2685,0.03431,0.02897,-0.0179,0.0061,1.0000 11.000,1.2816,0.03571,0.03038,-0.0153,0.0059,1.0000 11.500,1.3104,0.03993,0.03491,-0.0108,0.0053,1.0000 17.000,0.8574,0.14013,0.13848,-0.0212,0.0071,1.0000 17.250,0.8326,0.14836,0.14680,-0.0258,0.0074,1.0000 17.500,0.8079,0.15742,0.15593,-0.0306,0.0077,1.0000