Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-raf25-il-50000 Airfoil,raf25-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,28.3035 Max Cl/Cd alpha,4 Url,http://airfoiltools.com/polar/csv?polar=xf-raf25-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.5492,0.09987,0.09291,0.0074,1.0000,0.2792 -8.000,-0.5489,0.09702,0.09011,0.0077,1.0000,0.2964 -7.750,-0.5539,0.09461,0.08780,0.0078,1.0000,0.3123 -7.500,-0.5384,0.09018,0.08338,0.0094,1.0000,0.3321 -7.250,-0.5353,0.08713,0.08038,0.0104,1.0000,0.3516 -7.000,-0.5440,0.08489,0.07827,0.0114,1.0000,0.3700 -6.750,-0.5251,0.08071,0.07406,0.0132,1.0000,0.3928 -6.500,-0.5193,0.07744,0.07085,0.0149,1.0000,0.4156 -6.250,-0.5152,0.07449,0.06796,0.0171,1.0000,0.4420 -6.000,-0.5022,0.07132,0.06475,0.0198,1.0000,0.4764 -5.500,-0.5114,0.04569,0.03763,-0.0300,1.0000,0.1425 -5.250,-0.4916,0.04079,0.03203,-0.0302,1.0000,0.1296 -5.000,-0.4710,0.03677,0.02743,-0.0296,1.0000,0.1242 -4.750,-0.4497,0.03387,0.02406,-0.0287,1.0000,0.1284 -4.500,-0.4264,0.03109,0.02067,-0.0276,1.0000,0.1311 -4.250,-0.4013,0.02853,0.01751,-0.0264,1.0000,0.1329 -4.000,-0.3774,0.02625,0.01512,-0.0254,1.0000,0.1428 -3.750,-0.3525,0.02434,0.01303,-0.0244,1.0000,0.1559 -3.500,-0.3260,0.02247,0.01106,-0.0232,1.0000,0.1690 -3.250,-0.2995,0.02083,0.00948,-0.0224,1.0000,0.1990 -3.000,-0.2754,0.01890,0.00802,-0.0212,1.0000,0.2665 -2.750,-0.1714,0.01545,0.00684,-0.0289,1.0000,1.0000 -2.500,-0.1598,0.01512,0.00618,-0.0270,1.0000,1.0000 -2.250,-0.1446,0.01493,0.00566,-0.0254,1.0000,1.0000 -2.000,-0.1279,0.01481,0.00526,-0.0238,1.0000,1.0000 -1.750,-0.1100,0.01474,0.00493,-0.0223,1.0000,1.0000 -1.500,-0.0915,0.01470,0.00462,-0.0209,1.0000,1.0000 -1.250,-0.0724,0.01470,0.00442,-0.0196,1.0000,1.0000 -1.000,-0.0531,0.01472,0.00427,-0.0183,1.0000,1.0000 -0.750,-0.0337,0.01477,0.00418,-0.0170,1.0000,1.0000 -0.500,-0.0141,0.01484,0.00413,-0.0158,1.0000,1.0000 -0.250,0.0055,0.01495,0.00411,-0.0146,1.0000,1.0000 0.000,0.0249,0.01507,0.00416,-0.0135,1.0000,1.0000 0.250,0.0444,0.01523,0.00425,-0.0124,1.0000,1.0000 0.500,0.0637,0.01542,0.00440,-0.0113,1.0000,1.0000 0.750,0.0828,0.01563,0.00459,-0.0102,1.0000,1.0000 1.000,0.1018,0.01588,0.00484,-0.0092,1.0000,1.0000 1.250,0.1206,0.01617,0.00514,-0.0082,1.0000,1.0000 1.500,0.1392,0.01649,0.00549,-0.0073,1.0000,1.0000 1.750,0.1575,0.01686,0.00591,-0.0065,1.0000,1.0000 2.000,0.1755,0.01728,0.00639,-0.0057,1.0000,1.0000 2.250,0.1931,0.01775,0.00698,-0.0050,1.0000,1.0000 2.500,0.2104,0.01828,0.00761,-0.0044,1.0000,1.0000 2.750,0.2270,0.01889,0.00833,-0.0039,1.0000,1.0000 3.000,0.2432,0.01957,0.00914,-0.0035,1.0000,1.0000 3.250,0.2588,0.02034,0.01006,-0.0032,1.0000,1.0000 3.500,0.2737,0.02122,0.01111,-0.0031,1.0000,1.0000 3.750,0.3772,0.02285,0.01356,-0.0191,0.9556,1.0000 4.000,0.5372,0.01898,0.00875,-0.0206,0.3109,1.0000 4.250,0.5521,0.02207,0.01056,-0.0184,0.1942,1.0000 4.500,0.5772,0.02409,0.01239,-0.0173,0.1568,1.0000 4.750,0.6077,0.02641,0.01460,-0.0166,0.1380,1.0000 5.000,0.6366,0.02870,0.01705,-0.0159,0.1233,1.0000 5.250,0.6658,0.03125,0.01997,-0.0149,0.1183,1.0000 5.500,0.6919,0.03450,0.02326,-0.0143,0.1122,1.0000 5.750,0.7147,0.03702,0.02649,-0.0126,0.1086,1.0000 6.000,0.7370,0.04054,0.03050,-0.0113,0.1100,1.0000 6.250,0.7578,0.04424,0.03473,-0.0099,0.1138,1.0000 6.500,0.7734,0.04876,0.04006,-0.0084,0.1232,1.0000 6.750,0.7873,0.05387,0.04584,-0.0075,0.1370,1.0000 7.000,0.7953,0.06044,0.05317,-0.0081,0.1640,1.0000