Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-cp-100-050-gn-100000 Airfoil,cp-100-050-gn Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,31.3915 Max Cl/Cd alpha,9.5 Url,http://airfoiltools.com/polar/csv?polar=xf-cp-100-050-gn-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -5.000,-0.3984,0.12827,0.12347,-0.0080,1.0000,0.0645 -4.750,-0.4084,0.12754,0.12277,-0.0063,1.0000,0.0651 -4.500,-0.4202,0.12725,0.12253,-0.0052,1.0000,0.0655 -4.250,-0.4260,0.12707,0.12236,-0.0071,1.0000,0.0657 -4.000,-0.4251,0.12454,0.11986,-0.0070,1.0000,0.0659 -3.750,-0.4227,0.12114,0.11649,-0.0048,1.0000,0.0662 -3.500,-0.4195,0.11843,0.11381,-0.0040,0.9997,0.0668 -3.250,-0.4057,0.11579,0.11117,-0.0062,0.9966,0.0676 -3.000,-0.3906,0.11343,0.10881,-0.0091,0.9936,0.0686 -2.750,-0.3800,0.11112,0.10649,-0.0112,0.9905,0.0696 -2.500,-0.3528,0.10899,0.10431,-0.0183,0.9849,0.0716 -2.250,-0.3250,0.10743,0.10269,-0.0276,0.9815,0.0725 -2.000,-0.3174,0.10387,0.09916,-0.0261,0.9768,0.0730 -1.750,-0.2975,0.10112,0.09642,-0.0283,0.9727,0.0741 -1.500,-0.2849,0.09895,0.09425,-0.0297,0.9701,0.0751 -1.250,-0.2625,0.09645,0.09173,-0.0333,0.9632,0.0768 -1.000,-0.1934,0.09564,0.09070,-0.0510,0.9586,0.0800 -0.750,-0.1963,0.09251,0.08764,-0.0473,0.9569,0.0805 -0.500,-0.1834,0.08966,0.08483,-0.0472,0.9496,0.0814 -0.250,-0.1470,0.08768,0.08281,-0.0524,0.9446,0.0838 0.000,-0.1302,0.08595,0.08107,-0.0543,0.9428,0.0858 0.250,-0.0719,0.08482,0.07974,-0.0665,0.9345,0.0889 0.500,-0.0428,0.08197,0.07694,-0.0687,0.9291,0.0903 0.750,-0.0368,0.08023,0.07523,-0.0674,0.9274,0.0917 1.000,-0.0052,0.07839,0.07334,-0.0711,0.9174,0.0955 1.250,0.0585,0.07746,0.07225,-0.0820,0.9125,0.0996 1.500,0.1348,0.07186,0.06657,-0.0903,0.8668,0.1049 1.750,0.1946,0.07087,0.06539,-0.0991,0.8602,0.1109 2.000,0.2023,0.06926,0.06387,-0.0974,0.8543,0.1127 2.250,0.2394,0.06797,0.06255,-0.1008,0.8491,0.1186 2.500,0.2909,0.06692,0.06137,-0.1070,0.8437,0.1245 2.750,0.2967,0.06607,0.06059,-0.1052,0.8377,0.1267 3.000,0.3504,0.06638,0.06067,-0.1113,0.8322,0.1372 3.250,0.3925,0.06358,0.05800,-0.1143,0.8278,0.1419 3.500,0.4414,0.06114,0.05546,-0.1176,0.8070,0.1545 3.750,0.5907,0.05131,0.04543,-0.1312,0.7765,0.1865 4.000,0.6471,0.04678,0.04093,-0.1336,0.7606,0.2056 4.250,0.7426,0.03798,0.03212,-0.1383,0.7352,0.2560 4.500,0.7873,0.03231,0.02646,-0.1364,0.6927,0.2938 4.750,0.8264,0.02863,0.02133,-0.1337,0.4490,0.3503 5.000,0.7970,0.03201,0.02317,-0.1253,0.1664,0.3534 5.250,0.8035,0.03256,0.02338,-0.1221,0.1211,0.3989 5.500,0.8168,0.03221,0.02304,-0.1197,0.1127,0.4397 5.750,0.8322,0.03203,0.02288,-0.1177,0.1079,0.4819 6.000,0.8472,0.03199,0.02285,-0.1157,0.1046,0.5112 6.250,0.8622,0.03251,0.02334,-0.1138,0.1022,0.5263 6.500,0.8814,0.03326,0.02406,-0.1124,0.1005,0.5230 6.750,0.9023,0.03434,0.02505,-0.1114,0.0988,0.4841 7.000,0.9484,0.03615,0.02592,-0.1125,0.0970,0.1931 7.250,0.9674,0.03663,0.02620,-0.1107,0.0951,0.1770 7.500,0.9880,0.03722,0.02650,-0.1089,0.0931,0.1657 7.750,1.0134,0.03755,0.02665,-0.1080,0.0918,0.1599 8.000,1.0514,0.03794,0.02665,-0.1084,0.0908,0.1530 8.250,1.1054,0.03842,0.02682,-0.1111,0.0901,0.1513 8.500,1.1734,0.03911,0.02732,-0.1162,0.0899,0.1565 8.750,1.2524,0.04065,0.02868,-0.1234,0.0895,0.1642 9.000,1.3016,0.04207,0.03015,-0.1264,0.0890,0.1735 9.250,1.3683,0.04458,0.03276,-0.1326,0.0896,0.2093 9.500,1.3919,0.04434,0.03354,-0.1311,0.0907,1.0000 9.750,1.4134,0.04562,0.03511,-0.1287,0.0938,1.0000 10.000,1.4582,0.04884,0.03853,-0.1307,0.0986,1.0000 10.250,1.5172,0.05406,0.04366,-0.1359,0.1028,1.0000 10.500,1.5139,0.05405,0.04447,-0.1285,0.1106,1.0000 13.250,1.0761,0.14245,0.13727,-0.1077,0.2906,0.1761 13.500,0.8785,0.15007,0.14547,-0.1025,0.2570,0.1655 13.750,0.8719,0.15318,0.14856,-0.1032,0.2433,0.1666 14.000,1.0751,0.15213,0.14689,-0.1073,0.2405,0.2064 14.250,1.1355,0.14972,0.14517,-0.1004,0.2354,1.0000 14.500,0.9262,0.16073,0.15612,-0.0996,0.2161,0.2018 14.750,0.9020,0.16338,0.15878,-0.1026,0.2020,0.1964