Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ah21-9-il-200000 Airfoil,ah21-9-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,73.5028 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-ah21-9-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.5012,0.08699,0.08349,-0.0263,1.0000,0.0409 -8.000,-0.5113,0.08385,0.08042,-0.0269,1.0000,0.0418 -7.750,-0.5231,0.08072,0.07737,-0.0277,1.0000,0.0422 -7.500,-0.5299,0.07600,0.07264,-0.0326,1.0000,0.0431 -7.000,-0.5349,0.06823,0.06453,-0.0373,1.0000,0.0442 -6.750,-0.5400,0.06196,0.05815,-0.0378,1.0000,0.0448 -6.500,-0.5353,0.05776,0.05409,-0.0364,1.0000,0.0461 -6.250,-0.5278,0.05524,0.05158,-0.0350,1.0000,0.0476 -6.000,-0.5191,0.05227,0.04853,-0.0344,1.0000,0.0501 -5.750,-0.5028,0.04989,0.04551,-0.0352,1.0000,0.0569 -5.500,-0.4953,0.04371,0.03919,-0.0354,1.0000,0.0588 -5.250,-0.4816,0.04102,0.03656,-0.0345,1.0000,0.0614 -5.000,-0.4645,0.03820,0.03324,-0.0344,1.0000,0.0723 -4.750,-0.4482,0.03583,0.03099,-0.0337,1.0000,0.0768 -4.500,-0.4286,0.03305,0.02783,-0.0334,1.0000,0.0873 -4.250,-0.4080,0.03108,0.02555,-0.0330,1.0000,0.0999 -4.000,-0.3670,0.02271,0.01582,-0.0312,1.0000,0.0415 -3.750,-0.3411,0.02084,0.01357,-0.0305,1.0000,0.0420 -3.500,-0.3155,0.01931,0.01174,-0.0297,1.0000,0.0425 -3.250,-0.2898,0.01781,0.00998,-0.0290,1.0000,0.0425 -3.000,-0.2649,0.01671,0.00874,-0.0282,1.0000,0.0432 -2.750,-0.2406,0.01596,0.00789,-0.0274,1.0000,0.0444 -2.500,-0.2165,0.01475,0.00673,-0.0269,1.0000,0.0494 -2.250,-0.1925,0.01416,0.00613,-0.0262,1.0000,0.0525 -2.000,-0.1684,0.01373,0.00561,-0.0255,1.0000,0.0570 -1.750,-0.1437,0.01309,0.00504,-0.0251,1.0000,0.0771 -1.500,-0.1236,0.01059,0.00507,-0.0245,1.0000,0.6538 -1.250,-0.1120,0.01018,0.00537,-0.0199,1.0000,0.8818 -1.000,-0.0737,0.01007,0.00519,-0.0224,1.0000,1.0000 -0.750,-0.0507,0.01023,0.00519,-0.0218,1.0000,1.0000 -0.500,-0.0279,0.01041,0.00525,-0.0213,1.0000,1.0000 -0.250,0.0092,0.01073,0.00546,-0.0237,0.9960,1.0000 0.000,0.0491,0.01104,0.00566,-0.0266,0.9905,1.0000 0.250,0.0906,0.01136,0.00591,-0.0297,0.9849,1.0000 0.500,0.1296,0.01158,0.00608,-0.0324,0.9784,1.0000 0.750,0.1725,0.01180,0.00627,-0.0357,0.9721,1.0000 1.000,0.2122,0.01191,0.00636,-0.0383,0.9641,1.0000 1.250,0.2594,0.01200,0.00646,-0.0423,0.9576,1.0000 1.500,0.2994,0.01192,0.00641,-0.0447,0.9476,1.0000 1.750,0.3453,0.01174,0.00630,-0.0481,0.9382,1.0000 2.000,0.4001,0.01135,0.00599,-0.0531,0.9297,1.0000 2.250,0.4438,0.01089,0.00564,-0.0556,0.9175,1.0000 2.500,0.4907,0.01026,0.00513,-0.0586,0.9043,1.0000 2.750,0.5332,0.00964,0.00462,-0.0604,0.8861,1.0000 3.000,0.5704,0.00916,0.00423,-0.0613,0.8592,1.0000 3.250,0.6108,0.00877,0.00389,-0.0628,0.8096,1.0000 3.500,0.6505,0.00885,0.00357,-0.0639,0.6878,1.0000 3.750,0.6622,0.00987,0.00372,-0.0601,0.5156,1.0000 4.000,0.6697,0.01119,0.00415,-0.0562,0.3421,1.0000 4.250,0.6816,0.01261,0.00477,-0.0536,0.1894,1.0000 4.500,0.6988,0.01379,0.00550,-0.0519,0.1156,1.0000 4.750,0.7188,0.01474,0.00629,-0.0505,0.0868,1.0000 5.000,0.7391,0.01570,0.00714,-0.0491,0.0700,1.0000 5.250,0.7607,0.01664,0.00812,-0.0478,0.0607,1.0000 5.500,0.7817,0.01811,0.00956,-0.0466,0.0547,1.0000 5.750,0.8058,0.01895,0.01053,-0.0457,0.0491,1.0000 6.000,0.8294,0.02040,0.01197,-0.0451,0.0449,1.0000 6.250,0.8555,0.02263,0.01438,-0.0445,0.0426,1.0000 6.500,0.8807,0.02420,0.01622,-0.0437,0.0406,1.0000 6.750,0.9040,0.02550,0.01774,-0.0427,0.0371,1.0000 7.000,0.9265,0.02758,0.02012,-0.0417,0.0355,1.0000 7.250,0.9468,0.03021,0.02305,-0.0403,0.0342,1.0000 7.500,0.9604,0.03475,0.02796,-0.0385,0.0327,1.0000 7.750,0.9716,0.03748,0.03127,-0.0357,0.0312,1.0000 8.000,0.9788,0.04196,0.03622,-0.0329,0.0314,1.0000 8.250,0.9891,0.04660,0.04113,-0.0309,0.0329,1.0000 15.250,0.8688,0.19809,0.19461,-0.0755,0.0319,1.0000 15.500,0.8709,0.20156,0.19806,-0.0792,0.0316,1.0000