Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-lrn1007-il-100000-n5 Airfoil,lrn1007-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,55.3105 Max Cl/Cd alpha,6 Url,http://airfoiltools.com/polar/csv?polar=xf-lrn1007-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.1155,0.10680,0.10153,-0.0853,0.8964,0.0121 -8.500,-0.1064,0.10444,0.09918,-0.0870,0.8944,0.0121 -8.250,-0.0976,0.10234,0.09710,-0.0890,0.8922,0.0122 -8.000,-0.0864,0.09984,0.09460,-0.0914,0.8904,0.0122 -7.750,-0.0742,0.09722,0.09196,-0.0938,0.8890,0.0122 -7.500,-0.0616,0.09492,0.08967,-0.0967,0.8872,0.0122 -7.250,-0.0491,0.09222,0.08697,-0.0989,0.8852,0.0122 -7.000,-0.0375,0.08905,0.08385,-0.1010,0.8828,0.0123 -6.750,-0.0333,0.08338,0.07821,-0.0991,0.8812,0.0128 -6.500,-0.0232,0.07996,0.07479,-0.0996,0.8793,0.0131 -6.250,-0.0151,0.07630,0.07115,-0.0992,0.8777,0.0140 -6.000,-0.0018,0.07364,0.06838,-0.1013,0.8759,0.0145 -5.750,0.0101,0.07137,0.06612,-0.1033,0.8732,0.0150 -5.500,0.0232,0.06910,0.06385,-0.1055,0.8704,0.0155 -5.250,0.0387,0.06672,0.06145,-0.1080,0.8678,0.0161 -5.000,0.0569,0.06427,0.05898,-0.1109,0.8656,0.0166 -4.750,0.0772,0.06180,0.05644,-0.1139,0.8638,0.0174 -4.500,0.0990,0.05935,0.05392,-0.1170,0.8619,0.0183 -4.250,0.1149,0.05744,0.05198,-0.1186,0.8582,0.0196 -4.000,0.1366,0.05536,0.04981,-0.1209,0.8553,0.0210 -3.750,0.1653,0.05351,0.04782,-0.1240,0.8531,0.0227 -3.500,0.2040,0.05285,0.04685,-0.1278,0.8512,0.0240 -3.250,0.2387,0.05193,0.04561,-0.1303,0.8495,0.0244 -3.000,0.2471,0.04815,0.04192,-0.1300,0.8456,0.0253 -2.750,0.2581,0.04493,0.03877,-0.1300,0.8423,0.0279 -2.500,0.2842,0.04296,0.03665,-0.1313,0.8397,0.0319 -2.000,0.3470,0.03898,0.03223,-0.1348,0.8362,0.0426 -1.750,0.3712,0.04114,0.03382,-0.1330,0.8304,0.0505 -1.250,0.4240,0.03585,0.02824,-0.1350,0.8250,0.0650 -0.750,0.4718,0.03235,0.02450,-0.1357,0.8186,0.0977 -0.250,0.5256,0.02990,0.02161,-0.1364,0.8123,0.1601 0.250,0.5844,0.02889,0.02017,-0.1344,0.8055,0.0974 0.750,0.6430,0.02812,0.01900,-0.1321,0.7985,0.0299 1.250,0.6919,0.02721,0.01793,-0.1302,0.7891,0.0188 1.500,0.7213,0.02647,0.01715,-0.1298,0.7857,0.0160 1.750,0.7533,0.02580,0.01634,-0.1299,0.7835,0.0143 2.000,0.7714,0.02594,0.01632,-0.1285,0.7756,0.0138 2.250,0.8031,0.02557,0.01569,-0.1288,0.7722,0.0227 2.500,0.8377,0.02512,0.01503,-0.1294,0.7699,0.0457 2.750,0.8564,0.02401,0.01540,-0.1285,0.7614,1.0000 3.000,0.8873,0.02383,0.01507,-0.1286,0.7578,1.0000 3.250,0.9052,0.02418,0.01539,-0.1272,0.7490,1.0000 3.750,0.9525,0.02427,0.01549,-0.1258,0.7351,1.0000 4.000,0.9833,0.02389,0.01516,-0.1259,0.7308,1.0000 4.250,0.9994,0.02417,0.01549,-0.1242,0.7196,1.0000 4.500,1.0171,0.02435,0.01573,-0.1228,0.7088,1.0000 4.750,1.0453,0.02392,0.01536,-0.1224,0.7023,1.0000 5.000,1.0635,0.02399,0.01552,-0.1210,0.6905,1.0000 5.250,1.0804,0.02409,0.01574,-0.1193,0.6776,1.0000 5.500,1.0985,0.02404,0.01581,-0.1176,0.6649,1.0000 5.750,1.1201,0.02381,0.01576,-0.1162,0.6520,1.0000 6.000,1.1488,0.02077,0.01029,-0.1093,0.3345,1.0000 6.250,1.1389,0.02331,0.01163,-0.1043,0.1771,1.0000 6.500,1.1287,0.02663,0.01360,-0.0997,0.0057,1.0000 6.750,1.1445,0.02762,0.01481,-0.0980,0.0047,1.0000 7.000,1.1589,0.02877,0.01626,-0.0960,0.0043,1.0000 7.250,1.1718,0.03009,0.01789,-0.0940,0.0042,1.0000 7.500,1.1832,0.03158,0.01968,-0.0918,0.0042,1.0000 7.750,1.1925,0.03327,0.02166,-0.0894,0.0042,1.0000 8.000,1.1989,0.03523,0.02391,-0.0869,0.0043,1.0000 8.250,1.2030,0.03743,0.02635,-0.0842,0.0045,1.0000 8.500,1.2070,0.03975,0.02888,-0.0815,0.0046,1.0000 8.750,1.2142,0.04223,0.03154,-0.0790,0.0049,1.0000 9.750,1.3281,0.07047,0.06320,-0.0695,0.0228,1.0000 10.000,1.3121,0.07367,0.06674,-0.0654,0.0232,1.0000 10.250,1.2951,0.07698,0.07039,-0.0621,0.0239,1.0000 10.500,1.2781,0.08086,0.07454,-0.0596,0.0241,1.0000 10.750,1.2605,0.08495,0.07889,-0.0578,0.0244,1.0000 11.000,1.2422,0.08935,0.08352,-0.0567,0.0245,1.0000 11.250,1.2238,0.09399,0.08837,-0.0563,0.0245,1.0000 11.500,1.2052,0.09893,0.09349,-0.0566,0.0244,1.0000