Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca22112-jf-50000 Airfoil,naca22112-jf Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,23.8654 Max Cl/Cd alpha,4.25 Url,http://www.airfoiltools.com/polar/csv?polar=xf-naca22112-jf-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.000,-0.6740,0.06513,0.05795,-0.0169,1.0000,0.1816 -7.750,-0.6816,0.05884,0.05123,-0.0171,1.0000,0.1651 -7.500,-0.6868,0.05369,0.04537,-0.0157,1.0000,0.1526 -7.250,-0.6742,0.04979,0.04128,-0.0144,1.0000,0.1485 -7.000,-0.6675,0.04593,0.03671,-0.0122,1.0000,0.1415 -6.750,-0.6526,0.04312,0.03336,-0.0102,1.0000,0.1376 -6.500,-0.6335,0.04014,0.03014,-0.0087,1.0000,0.1349 -6.250,-0.6137,0.03753,0.02718,-0.0071,1.0000,0.1328 -6.000,-0.5928,0.03532,0.02465,-0.0055,1.0000,0.1333 -5.750,-0.5704,0.03337,0.02241,-0.0041,1.0000,0.1349 -5.500,-0.5459,0.03155,0.02032,-0.0028,1.0000,0.1362 -5.250,-0.5193,0.02989,0.01845,-0.0018,1.0000,0.1375 -5.000,-0.4915,0.02822,0.01680,-0.0010,1.0000,0.1419 -4.750,-0.4645,0.02686,0.01550,-0.0002,1.0000,0.1485 -4.500,-0.4378,0.02576,0.01433,0.0010,1.0000,0.1545 -4.250,-0.4154,0.02455,0.01328,0.0023,1.0000,0.1647 -4.000,-0.3957,0.02347,0.01232,0.0040,1.0000,0.1792 -3.750,-0.3775,0.02230,0.01138,0.0058,1.0000,0.2024 -3.500,-0.3672,0.02025,0.01057,0.0084,1.0000,0.3321 -3.250,-0.3645,0.01897,0.01113,0.0159,1.0000,0.6711 -3.000,-0.3380,0.02039,0.01289,0.0237,1.0000,0.8420 -2.750,-0.0291,0.02367,0.01455,-0.0152,1.0000,0.9891 -2.500,0.0115,0.02267,0.01340,-0.0200,1.0000,1.0000 -2.250,0.0206,0.02207,0.01277,-0.0189,1.0000,1.0000 -2.000,0.0274,0.02158,0.01226,-0.0173,1.0000,1.0000 -1.750,0.0305,0.02121,0.01190,-0.0150,1.0000,1.0000 -1.500,0.0289,0.02097,0.01168,-0.0119,1.0000,1.0000 -1.250,0.0220,0.02087,0.01159,-0.0080,1.0000,1.0000 -1.000,0.0097,0.02091,0.01163,-0.0032,1.0000,1.0000 -0.750,-0.0051,0.02106,0.01178,0.0018,1.0000,1.0000 -0.500,-0.0186,0.02133,0.01201,0.0065,1.0000,1.0000 -0.250,-0.0280,0.02170,0.01233,0.0104,1.0000,1.0000 0.000,-0.0329,0.02217,0.01274,0.0135,1.0000,1.0000 0.250,0.0339,0.02304,0.01355,0.0041,0.9805,1.0000 0.500,0.1282,0.02362,0.01414,-0.0093,0.9489,1.0000 0.750,0.2357,0.02352,0.01412,-0.0237,0.9144,1.0000 1.000,0.3280,0.02269,0.01339,-0.0335,0.8763,1.0000 1.250,0.3742,0.02214,0.01284,-0.0347,0.8352,1.0000 1.500,0.4043,0.02177,0.01242,-0.0329,0.7954,1.0000 2.000,0.4460,0.02154,0.01196,-0.0265,0.7152,1.0000 2.250,0.4658,0.02158,0.01181,-0.0234,0.6750,1.0000 2.500,0.4845,0.02181,0.01185,-0.0204,0.6320,1.0000 2.750,0.5041,0.02210,0.01190,-0.0176,0.5908,1.0000 3.000,0.5233,0.02259,0.01218,-0.0152,0.5488,1.0000 3.250,0.5432,0.02316,0.01250,-0.0131,0.5109,1.0000 3.500,0.5637,0.02385,0.01301,-0.0113,0.4777,1.0000 3.750,0.5844,0.02463,0.01363,-0.0097,0.4493,1.0000 4.000,0.6058,0.02541,0.01424,-0.0082,0.4255,1.0000 4.250,0.6279,0.02631,0.01497,-0.0070,0.4063,1.0000 4.500,0.6491,0.02730,0.01596,-0.0058,0.3890,1.0000 4.750,0.6707,0.02828,0.01688,-0.0047,0.3737,1.0000 5.000,0.6908,0.02944,0.01815,-0.0035,0.3599,1.0000 5.250,0.7105,0.03081,0.01965,-0.0024,0.3486,1.0000 5.500,0.7316,0.03203,0.02087,-0.0014,0.3384,1.0000 5.750,0.7509,0.03337,0.02233,-0.0002,0.3281,1.0000 6.000,0.7685,0.03509,0.02423,0.0009,0.3201,1.0000 6.250,0.7869,0.03672,0.02601,0.0020,0.3123,1.0000 6.500,0.8034,0.03860,0.02804,0.0032,0.3051,1.0000 6.750,0.8168,0.04071,0.03040,0.0045,0.2976,1.0000 7.000,0.8397,0.04228,0.03190,0.0052,0.2919,1.0000 7.250,0.8396,0.04593,0.03608,0.0067,0.2873,1.0000 7.500,0.8452,0.04901,0.03944,0.0079,0.2819,1.0000 7.750,0.8704,0.05035,0.04069,0.0087,0.2757,1.0000 8.000,0.8556,0.05575,0.04654,0.0098,0.2741,1.0000 8.250,0.8338,0.06209,0.05317,0.0100,0.2737,1.0000 8.500,0.8071,0.06922,0.06045,0.0090,0.2746,1.0000 8.750,0.7825,0.07651,0.06781,0.0072,0.2765,1.0000