Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-dsma523b-il-50000 Airfoil,dsma523b-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,20.8618 Max Cl/Cd alpha,3.75 Url,http://airfoiltools.com/polar/csv?polar=xf-dsma523b-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.5156,0.11381,0.10577,0.0005,1.0000,0.3697 -8.500,-0.4790,0.10854,0.10044,0.0012,1.0000,0.3788 -8.250,-0.6937,0.07479,0.06680,-0.0363,1.0000,0.1778 -8.000,-0.6869,0.06967,0.06161,-0.0373,1.0000,0.1718 -7.750,-0.6969,0.05735,0.04810,-0.0511,1.0000,0.1572 -7.500,-0.6775,0.05275,0.04326,-0.0528,1.0000,0.1558 -7.250,-0.6533,0.04832,0.03836,-0.0558,1.0000,0.1559 -7.000,-0.6260,0.04429,0.03392,-0.0587,1.0000,0.1582 -6.750,-0.6014,0.04142,0.03097,-0.0594,1.0000,0.1615 -6.500,-0.5730,0.03870,0.02800,-0.0607,1.0000,0.1643 -6.250,-0.5436,0.03645,0.02545,-0.0619,1.0000,0.1702 -6.000,-0.5113,0.03431,0.02285,-0.0635,1.0000,0.1769 -5.750,-0.4873,0.03251,0.02116,-0.0627,1.0000,0.1838 -5.500,-0.4588,0.03113,0.01955,-0.0628,1.0000,0.1949 -5.250,-0.4372,0.02981,0.01841,-0.0610,1.0000,0.2055 -5.000,-0.4138,0.02872,0.01732,-0.0594,1.0000,0.2203 -4.750,-0.3917,0.02775,0.01647,-0.0575,1.0000,0.2400 -4.500,-0.3703,0.02665,0.01574,-0.0556,1.0000,0.2691 -4.250,-0.3427,0.02455,0.01478,-0.0557,1.0000,0.3696 -4.000,-0.3592,0.02575,0.01759,-0.0408,1.0000,0.5060 -3.750,-0.3520,0.02910,0.02081,-0.0313,1.0000,0.6321 -3.500,-0.3446,0.03089,0.02245,-0.0237,1.0000,0.6763 -3.250,-0.3393,0.03191,0.02339,-0.0160,1.0000,0.7109 -3.000,-0.3335,0.03242,0.02381,-0.0090,1.0000,0.7450 -2.750,-0.3300,0.03237,0.02369,-0.0015,1.0000,0.7742 -2.500,-0.3226,0.03197,0.02321,0.0043,1.0000,0.8036 -2.250,-0.3132,0.03142,0.02256,0.0091,1.0000,0.8336 -2.000,-0.3061,0.03046,0.02154,0.0148,1.0000,0.8626 -1.750,-0.2958,0.02940,0.02041,0.0192,1.0000,0.8932 -1.500,-0.2785,0.02818,0.01909,0.0222,1.0000,0.9234 -1.250,-0.0456,0.02724,0.01764,-0.0146,1.0000,1.0000 -1.000,-0.0364,0.02683,0.01723,-0.0125,1.0000,1.0000 -0.750,-0.0273,0.02645,0.01686,-0.0104,1.0000,1.0000 -0.500,-0.0182,0.02611,0.01654,-0.0082,1.0000,1.0000 -0.250,-0.0093,0.02579,0.01626,-0.0059,1.0000,1.0000 0.000,-0.0006,0.02550,0.01601,-0.0035,1.0000,1.0000 0.250,0.0080,0.02524,0.01579,-0.0012,1.0000,1.0000 0.500,0.0164,0.02499,0.01561,0.0012,1.0000,1.0000 0.750,0.0246,0.02477,0.01546,0.0036,1.0000,1.0000 1.000,0.0329,0.02457,0.01535,0.0060,1.0000,1.0000 1.250,0.0412,0.02441,0.01527,0.0083,1.0000,1.0000 1.500,0.0507,0.02429,0.01526,0.0103,1.0000,1.0000 1.750,0.0635,0.02429,0.01536,0.0116,1.0000,1.0000 2.000,0.0802,0.02441,0.01561,0.0121,1.0000,1.0000 2.250,0.1001,0.02467,0.01602,0.0120,1.0000,1.0000 2.500,0.1223,0.02505,0.01658,0.0114,1.0000,1.0000 2.750,0.1458,0.02557,0.01730,0.0103,1.0000,1.0000 3.000,0.1700,0.02624,0.01822,0.0089,1.0000,1.0000 3.250,0.5409,0.02667,0.01539,-0.0384,0.2318,1.0000 3.500,0.5778,0.02785,0.01651,-0.0400,0.2120,1.0000 3.750,0.6100,0.02924,0.01800,-0.0407,0.2011,1.0000 4.000,0.6348,0.03051,0.01927,-0.0403,0.1914,1.0000 4.250,0.6577,0.03209,0.02100,-0.0395,0.1844,1.0000 4.500,0.6782,0.03362,0.02284,-0.0381,0.1802,1.0000 4.750,0.6977,0.03526,0.02472,-0.0366,0.1761,1.0000 5.000,0.7184,0.03704,0.02655,-0.0357,0.1709,1.0000 5.250,0.7391,0.03974,0.02936,-0.0351,0.1673,1.0000 5.500,0.7587,0.04219,0.03223,-0.0340,0.1666,1.0000 5.750,0.7780,0.04503,0.03548,-0.0330,0.1665,1.0000 6.000,0.7953,0.04799,0.03888,-0.0320,0.1661,1.0000 6.250,0.8113,0.05123,0.04254,-0.0310,0.1657,1.0000 6.500,0.8289,0.05526,0.04685,-0.0307,0.1669,1.0000 6.750,0.8195,0.06046,0.05319,-0.0280,0.1805,1.0000 7.000,0.8417,0.06603,0.05878,-0.0290,0.1872,1.0000 7.250,0.6144,0.09744,0.09181,-0.0644,0.4639,1.0000 7.500,0.6272,0.10104,0.09541,-0.0643,0.4412,1.0000