Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-sc20404-il-100000-n5 Airfoil,sc20404-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,25.99 Max Cl/Cd alpha,1.75 Url,http://airfoiltools.com/polar/csv?polar=xf-sc20404-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.500,-0.6673,0.11671,0.11170,0.0232,1.0000,0.0301 -9.250,-0.6644,0.11267,0.10769,0.0212,1.0000,0.0303 -9.000,-0.6615,0.10859,0.10364,0.0191,1.0000,0.0304 -8.000,-0.5547,0.07829,0.07369,0.0001,1.0000,0.0189 -7.500,-0.6373,0.08004,0.07526,-0.0027,1.0000,0.0193 -7.250,-0.6287,0.07467,0.06985,-0.0075,1.0000,0.0184 -7.000,-0.6175,0.06914,0.06424,-0.0123,1.0000,0.0176 -6.750,-0.6036,0.06353,0.05852,-0.0169,1.0000,0.0168 -6.500,-0.5870,0.05794,0.05274,-0.0210,1.0000,0.0161 -6.250,-0.5676,0.05242,0.04696,-0.0244,1.0000,0.0154 -6.000,-0.5455,0.04712,0.04134,-0.0273,1.0000,0.0151 -5.750,-0.5210,0.04253,0.03637,-0.0294,1.0000,0.0167 -5.500,-0.4933,0.03823,0.03156,-0.0310,1.0000,0.0192 -5.250,-0.4646,0.03432,0.02708,-0.0321,1.0000,0.0204 -5.000,-0.4358,0.03012,0.02213,-0.0330,1.0000,0.0204 -4.750,-0.4063,0.02672,0.01814,-0.0335,1.0000,0.0206 -4.500,-0.3772,0.02395,0.01484,-0.0336,1.0000,0.0210 -4.250,-0.3487,0.02153,0.01203,-0.0334,1.0000,0.0217 -4.000,-0.3217,0.01892,0.00921,-0.0333,1.0000,0.0239 -3.750,-0.2947,0.01802,0.00815,-0.0332,1.0000,0.0325 -3.500,-0.2677,0.01639,0.00642,-0.0329,1.0000,0.0349 -3.250,-0.2400,0.01519,0.00512,-0.0330,1.0000,0.0400 -3.000,-0.2116,0.01423,0.00404,-0.0331,1.0000,0.0534 -2.750,-0.1834,0.01206,0.00317,-0.0345,1.0000,0.3216 -2.500,-0.1674,0.01078,0.00326,-0.0313,1.0000,0.7184 -2.250,-0.1526,0.01061,0.00325,-0.0272,1.0000,0.8070 -2.000,-0.1425,0.01039,0.00310,-0.0220,1.0000,0.8718 -1.750,-0.1290,0.01005,0.00277,-0.0179,1.0000,0.9231 -1.500,-0.1008,0.00980,0.00241,-0.0178,1.0000,0.9594 -1.250,-0.0703,0.00961,0.00212,-0.0186,1.0000,1.0000 -1.000,-0.0412,0.00958,0.00198,-0.0194,1.0000,1.0000 -0.750,-0.0122,0.00957,0.00186,-0.0201,1.0000,1.0000 -0.500,0.0166,0.00958,0.00180,-0.0207,1.0000,1.0000 -0.250,0.0451,0.00960,0.00179,-0.0212,1.0000,1.0000 0.000,0.0734,0.00963,0.00183,-0.0216,1.0000,1.0000 0.250,0.1014,0.00967,0.00191,-0.0219,1.0000,1.0000 0.500,0.1292,0.00973,0.00206,-0.0222,1.0000,1.0000 0.750,0.1569,0.00980,0.00222,-0.0224,1.0000,1.0000 1.000,0.1844,0.00988,0.00243,-0.0226,1.0000,1.0000 1.250,0.2117,0.00998,0.00270,-0.0227,1.0000,1.0000 1.500,0.2390,0.01009,0.00303,-0.0227,1.0000,1.0000 1.750,0.3111,0.01197,0.00311,-0.0297,0.3471,1.0000 2.000,0.3346,0.01418,0.00402,-0.0297,0.0547,1.0000 2.250,0.3620,0.01514,0.00507,-0.0294,0.0396,1.0000 2.500,0.3887,0.01622,0.00627,-0.0291,0.0344,1.0000 2.750,0.4148,0.01784,0.00798,-0.0286,0.0321,1.0000 3.000,0.4426,0.01944,0.00979,-0.0281,0.0295,1.0000 3.250,0.4699,0.02067,0.01117,-0.0280,0.0221,1.0000 3.750,0.5252,0.02645,0.01777,-0.0270,0.0201,1.0000 4.000,0.5525,0.02950,0.02139,-0.0264,0.0198,1.0000 4.250,0.5787,0.03310,0.02557,-0.0258,0.0196,1.0000 4.500,0.6031,0.03736,0.03053,-0.0253,0.0197,1.0000 4.750,0.6289,0.04103,0.03473,-0.0249,0.0185,1.0000 5.000,0.6535,0.04528,0.03946,-0.0248,0.0163,1.0000 5.250,0.6754,0.04978,0.04433,-0.0254,0.0148,1.0000 5.500,0.6952,0.05480,0.04966,-0.0263,0.0149,1.0000 5.750,0.7132,0.06007,0.05519,-0.0278,0.0155,1.0000 6.000,0.7290,0.06541,0.06074,-0.0298,0.0162,1.0000 6.250,0.7424,0.07078,0.06627,-0.0323,0.0171,1.0000 6.500,0.7531,0.07610,0.07170,-0.0349,0.0180,1.0000 6.750,0.7574,0.08121,0.07684,-0.0360,0.0195,1.0000 7.250,0.7793,0.09324,0.08907,-0.0478,0.0263,1.0000 7.750,0.7823,0.10305,0.09883,-0.0557,0.0278,1.0000 8.000,0.7832,0.10765,0.10340,-0.0587,0.0281,1.0000 8.250,0.7844,0.11214,0.10785,-0.0613,0.0283,1.0000