Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-rc0864c-il-500000-n5 Airfoil,rc0864c-il Reynolds number,500000 Ncrit,5 Mach,0 Max Cl/Cd,40.298 Max Cl/Cd alpha,4 Url,http://airfoiltools.com/polar/csv?polar=xf-rc0864c-il-500000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.5638,0.08390,0.08154,-0.0153,1.0000,0.0073 -8.250,-0.5681,0.07842,0.07608,-0.0208,1.0000,0.0073 -8.000,-0.5731,0.07325,0.07089,-0.0246,1.0000,0.0073 -7.750,-0.5730,0.06770,0.06527,-0.0277,1.0000,0.0074 -7.500,-0.5710,0.06239,0.05986,-0.0294,1.0000,0.0074 -7.250,-0.5677,0.05721,0.05454,-0.0298,1.0000,0.0074 -7.000,-0.5643,0.05213,0.04929,-0.0289,1.0000,0.0075 -6.750,-0.5610,0.04750,0.04446,-0.0270,1.0000,0.0075 -6.500,-0.5580,0.04358,0.04029,-0.0244,1.0000,0.0075 -6.250,-0.5543,0.04037,0.03684,-0.0214,1.0000,0.0075 -6.000,-0.5373,0.03594,0.03224,-0.0222,0.9973,0.0077 -5.750,-0.5136,0.03326,0.02941,-0.0236,0.9947,0.0078 -5.500,-0.4896,0.03105,0.02703,-0.0245,0.9913,0.0082 -5.250,-0.4628,0.02856,0.02429,-0.0253,0.9883,0.0090 -5.000,-0.4306,0.02630,0.02123,-0.0250,0.9857,0.0101 -4.750,-0.4065,0.02312,0.01773,-0.0248,0.9813,0.0103 -4.500,-0.3784,0.02077,0.01532,-0.0256,0.9784,0.0105 -4.250,-0.3485,0.01907,0.01343,-0.0263,0.9758,0.0108 -3.750,-0.2898,0.01611,0.00996,-0.0258,0.9671,0.0072 -3.500,-0.2595,0.01480,0.00852,-0.0263,0.9636,0.0070 -3.250,-0.2312,0.01379,0.00741,-0.0262,0.9584,0.0068 -3.000,-0.2028,0.01292,0.00645,-0.0261,0.9527,0.0067 -2.750,-0.1731,0.01215,0.00561,-0.0263,0.9480,0.0067 -2.500,-0.1470,0.01151,0.00492,-0.0258,0.9403,0.0067 -2.250,-0.1192,0.01093,0.00431,-0.0256,0.9336,0.0069 -2.000,-0.0932,0.01048,0.00383,-0.0250,0.9247,0.0071 -1.750,-0.0658,0.01016,0.00347,-0.0247,0.9165,0.0075 -1.500,-0.0411,0.00956,0.00290,-0.0240,0.9067,0.0082 -1.250,-0.0146,0.00929,0.00263,-0.0237,0.8973,0.0095 -1.000,0.0122,0.00907,0.00238,-0.0233,0.8876,0.0100 -0.750,0.0384,0.00881,0.00210,-0.0228,0.8763,0.0104 -0.500,0.0645,0.00862,0.00183,-0.0222,0.8589,0.0111 -0.250,0.0890,0.00855,0.00161,-0.0211,0.8179,0.0120 0.000,0.1139,0.00855,0.00144,-0.0202,0.7775,0.0145 0.250,0.1350,0.00802,0.00130,-0.0189,0.7241,0.2122 0.500,0.1398,0.00624,0.00121,-0.0146,0.6503,0.7878 0.750,0.1579,0.00642,0.00138,-0.0119,0.5602,0.8939 1.000,0.1788,0.00758,0.00169,-0.0105,0.3247,0.9424 1.250,0.2009,0.00915,0.00210,-0.0100,0.0141,0.9554 1.500,0.2363,0.00940,0.00234,-0.0115,0.0121,0.9715 1.750,0.2775,0.00972,0.00268,-0.0143,0.0109,0.9799 2.000,0.3092,0.00994,0.00291,-0.0151,0.0105,0.9828 2.250,0.3394,0.01021,0.00317,-0.0157,0.0101,0.9860 2.500,0.3720,0.01052,0.00347,-0.0169,0.0089,0.9877 2.750,0.4027,0.01108,0.00401,-0.0177,0.0080,0.9898 3.000,0.4337,0.01148,0.00441,-0.0185,0.0076,0.9923 3.250,0.4636,0.01192,0.00486,-0.0191,0.0073,0.9948 3.500,0.4946,0.01246,0.00542,-0.0199,0.0070,0.9964 3.750,0.5247,0.01307,0.00606,-0.0206,0.0067,0.9982 4.000,0.5545,0.01376,0.00678,-0.0211,0.0066,0.9999 4.250,0.5754,0.01442,0.00748,-0.0198,0.0065,1.0000 4.500,0.5960,0.01515,0.00825,-0.0183,0.0065,1.0000 4.750,0.6168,0.01595,0.00912,-0.0169,0.0065,1.0000 5.000,0.6379,0.01685,0.01010,-0.0154,0.0066,1.0000 5.250,0.6590,0.01785,0.01120,-0.0140,0.0067,1.0000 5.500,0.6800,0.01898,0.01248,-0.0126,0.0068,1.0000 5.750,0.7007,0.02026,0.01392,-0.0111,0.0070,1.0000 6.000,0.7207,0.02171,0.01554,-0.0095,0.0072,1.0000 6.250,0.7396,0.02338,0.01739,-0.0079,0.0074,1.0000 6.500,0.7576,0.02508,0.01931,-0.0062,0.0075,1.0000 6.750,0.7753,0.02660,0.02114,-0.0042,0.0072,1.0000 7.000,0.7923,0.02831,0.02312,-0.0024,0.0067,1.0000 7.250,0.8077,0.03030,0.02537,-0.0005,0.0065,1.0000 7.500,0.8200,0.03317,0.02858,0.0018,0.0066,1.0000 7.750,0.8297,0.03648,0.03222,0.0042,0.0067,1.0000 8.000,0.8362,0.04019,0.03626,0.0066,0.0069,1.0000 8.250,0.8393,0.04420,0.04058,0.0090,0.0071,1.0000