Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ys915-il-500000 Airfoil,ys915-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,91.8594 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-ys915-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.500,-0.4690,0.08618,0.08399,-0.0516,0.9935,0.0122 -9.250,-0.4657,0.07931,0.07713,-0.0572,0.9911,0.0122 -9.000,-0.4644,0.07139,0.06915,-0.0656,0.9883,0.0122 -8.750,-0.4671,0.06369,0.06135,-0.0766,0.9852,0.0121 -8.500,-0.4697,0.05880,0.05630,-0.0830,0.9821,0.0121 -8.250,-0.4784,0.05564,0.05300,-0.0826,0.9758,0.0122 -8.000,-0.4755,0.05150,0.04864,-0.0846,0.9727,0.0122 -7.750,-0.4671,0.04751,0.04437,-0.0862,0.9708,0.0122 -7.500,-0.4659,0.04486,0.04151,-0.0844,0.9671,0.0123 -7.250,-0.4654,0.04217,0.03860,-0.0817,0.9631,0.0123 -7.000,-0.4639,0.03716,0.03321,-0.0803,0.9604,0.0125 -5.750,-0.4128,0.02151,0.01606,-0.0677,0.9490,0.0094 -5.500,-0.3912,0.01870,0.01289,-0.0659,0.9479,0.0082 -5.250,-0.3669,0.01702,0.01103,-0.0650,0.9469,0.0082 -5.000,-0.3429,0.01601,0.00991,-0.0643,0.9461,0.0093 -4.750,-0.3162,0.01568,0.00953,-0.0643,0.9454,0.0114 -4.500,-0.2891,0.01509,0.00885,-0.0643,0.9447,0.0121 -4.250,-0.2796,0.01439,0.00806,-0.0606,0.9420,0.0121 -4.000,-0.2737,0.01389,0.00741,-0.0561,0.9383,0.0122 -3.750,-0.2546,0.01308,0.00639,-0.0543,0.9365,0.0139 -3.500,-0.2360,0.01157,0.00549,-0.0528,0.9349,0.1843 -3.250,-0.2127,0.01087,0.00542,-0.0526,0.9338,0.3547 -3.000,-0.1842,0.01070,0.00541,-0.0531,0.9329,0.4121 -2.750,-0.1534,0.01061,0.00536,-0.0539,0.9322,0.4404 -2.500,-0.1224,0.01053,0.00533,-0.0548,0.9316,0.4680 -2.250,-0.1108,0.01063,0.00542,-0.0516,0.9279,0.4843 -2.000,-0.0926,0.01064,0.00547,-0.0497,0.9247,0.5017 -1.750,-0.0658,0.01057,0.00545,-0.0497,0.9229,0.5234 -1.500,-0.0365,0.01047,0.00543,-0.0502,0.9215,0.5489 -1.250,-0.0058,0.01034,0.00540,-0.0511,0.9204,0.5807 -1.000,0.0263,0.01018,0.00535,-0.0521,0.9195,0.6193 -0.750,0.0590,0.00999,0.00534,-0.0533,0.9188,0.6640 -0.500,0.0707,0.01001,0.00552,-0.0499,0.9140,0.7097 -0.250,0.0908,0.00986,0.00561,-0.0483,0.9104,0.7694 0.000,0.1211,0.00959,0.00563,-0.0486,0.9088,0.8470 0.500,0.2755,0.00911,0.00544,-0.0702,0.9177,0.9434 0.750,0.3102,0.00927,0.00564,-0.0718,0.9132,0.9651 1.000,0.3542,0.00908,0.00552,-0.0752,0.9109,0.9764 1.250,0.4009,0.00872,0.00520,-0.0789,0.9084,0.9826 1.500,0.4537,0.00803,0.00456,-0.0835,0.9047,0.9834 1.750,0.4963,0.00724,0.00379,-0.0856,0.8894,0.9865 2.000,0.5323,0.00651,0.00305,-0.0861,0.8584,0.9921 2.250,0.5705,0.00625,0.00283,-0.0880,0.8299,0.9974 2.500,0.5879,0.00640,0.00241,-0.0852,0.6780,1.0000 2.750,0.5769,0.00768,0.00278,-0.0772,0.4854,1.0000 3.000,0.5625,0.00956,0.00331,-0.0692,0.1951,1.0000 3.250,0.5659,0.01090,0.00386,-0.0647,0.0292,1.0000 3.500,0.5816,0.01154,0.00454,-0.0620,0.0131,1.0000 3.750,0.5966,0.01228,0.00537,-0.0591,0.0108,1.0000 4.000,0.6061,0.01369,0.00692,-0.0551,0.0097,1.0000 4.250,0.6236,0.01471,0.00801,-0.0528,0.0097,1.0000 4.500,0.6452,0.01587,0.00928,-0.0513,0.0100,1.0000 4.750,0.6693,0.01676,0.01026,-0.0503,0.0107,1.0000 5.750,0.7703,0.02732,0.02197,-0.0445,0.0153,1.0000 6.000,0.7864,0.02909,0.02398,-0.0418,0.0133,1.0000 6.250,0.7997,0.03092,0.02601,-0.0391,0.0120,1.0000