Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca000834-il-100000-n5 Airfoil,naca000834-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,30.0879 Max Cl/Cd alpha,2.75 Url,http://airfoiltools.com/polar/csv?polar=xf-naca000834-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.500,-0.5190,0.09074,0.08620,-0.0148,1.0000,0.0483 -9.250,-0.5249,0.08592,0.08141,-0.0166,1.0000,0.0487 -9.000,-0.5326,0.08082,0.07635,-0.0188,1.0000,0.0490 -8.750,-0.5428,0.07535,0.07090,-0.0218,1.0000,0.0493 -8.500,-0.5577,0.06966,0.06523,-0.0257,1.0000,0.0495 -8.250,-0.5743,0.06497,0.06050,-0.0274,1.0000,0.0497 -8.000,-0.5904,0.06090,0.05638,-0.0271,1.0000,0.0499 -7.500,-0.6126,0.05027,0.04531,-0.0254,1.0000,0.0328 -7.250,-0.6142,0.04494,0.03991,-0.0240,1.0000,0.0275 -7.000,-0.6598,0.05371,0.04795,-0.0187,1.0000,0.0222 -6.750,-0.6535,0.04974,0.04373,-0.0171,1.0000,0.0207 -6.500,-0.6449,0.04577,0.03936,-0.0151,1.0000,0.0191 -6.250,-0.6340,0.04177,0.03489,-0.0125,1.0000,0.0176 -6.000,-0.6193,0.03831,0.03080,-0.0095,1.0000,0.0162 -5.750,-0.6022,0.03594,0.02798,-0.0072,1.0000,0.0157 -4.750,-0.5275,0.02534,0.01593,-0.0001,1.0000,0.0171 -4.500,-0.5056,0.02364,0.01405,0.0011,1.0000,0.0191 -4.250,-0.4826,0.02188,0.01210,0.0025,1.0000,0.0201 -4.000,-0.4612,0.02034,0.01039,0.0041,1.0000,0.0213 -3.750,-0.4414,0.01913,0.00904,0.0059,1.0000,0.0234 -3.500,-0.4232,0.01794,0.00779,0.0076,1.0000,0.0281 -3.250,-0.4031,0.01705,0.00668,0.0093,1.0000,0.0330 -3.000,-0.3829,0.01605,0.00566,0.0108,1.0000,0.0505 -2.750,-0.3766,0.01252,0.00490,0.0139,1.0000,0.5745 -2.500,-0.3383,0.01283,0.00615,0.0171,1.0000,0.9063 -2.250,-0.3029,0.01293,0.00592,0.0158,1.0000,0.9278 -2.000,-0.2638,0.01299,0.00569,0.0135,1.0000,0.9424 -1.750,-0.2245,0.01301,0.00544,0.0109,1.0000,0.9553 -1.500,-0.1824,0.01300,0.00523,0.0076,1.0000,0.9657 -1.250,-0.1395,0.01297,0.00500,0.0040,1.0000,0.9747 -1.000,-0.0977,0.01291,0.00483,0.0005,1.0000,0.9838 -0.750,-0.0558,0.01284,0.00467,-0.0031,1.0000,0.9925 -0.500,-0.0159,0.01275,0.00453,-0.0063,1.0000,1.0000 -0.250,-0.0076,0.01270,0.00447,-0.0032,1.0000,1.0000 0.000,0.0000,0.01268,0.00445,0.0000,1.0000,1.0000 0.250,0.0076,0.01270,0.00447,0.0032,1.0000,1.0000 0.500,0.0159,0.01275,0.00453,0.0063,1.0000,1.0000 0.750,0.0557,0.01283,0.00467,0.0031,0.9925,1.0000 1.000,0.0976,0.01291,0.00482,-0.0005,0.9839,1.0000 1.250,0.1394,0.01296,0.00500,-0.0040,0.9747,1.0000 1.500,0.1824,0.01300,0.00522,-0.0076,0.9657,1.0000 1.750,0.2244,0.01301,0.00543,-0.0109,0.9553,1.0000 2.000,0.2637,0.01299,0.00568,-0.0135,0.9425,1.0000 2.250,0.3027,0.01293,0.00592,-0.0158,0.9278,1.0000 2.500,0.3381,0.01283,0.00614,-0.0171,0.9063,1.0000 2.750,0.3764,0.01251,0.00490,-0.0139,0.5767,1.0000 3.000,0.3826,0.01604,0.00565,-0.0107,0.0507,1.0000 3.250,0.4028,0.01704,0.00667,-0.0092,0.0330,1.0000 3.500,0.4229,0.01793,0.00778,-0.0076,0.0281,1.0000 3.750,0.4411,0.01912,0.00904,-0.0059,0.0234,1.0000 4.000,0.4609,0.02033,0.01038,-0.0041,0.0213,1.0000 4.250,0.4824,0.02187,0.01209,-0.0025,0.0201,1.0000 4.500,0.5054,0.02363,0.01404,-0.0011,0.0191,1.0000 4.750,0.5273,0.02533,0.01593,0.0002,0.0171,1.0000 5.000,0.5470,0.02813,0.01897,0.0015,0.0156,1.0000 5.500,0.5847,0.03352,0.02515,0.0052,0.0155,1.0000 5.750,0.6021,0.03593,0.02796,0.0073,0.0157,1.0000 6.000,0.6193,0.03831,0.03079,0.0096,0.0162,1.0000 6.250,0.6340,0.04177,0.03488,0.0125,0.0176,1.0000 6.500,0.6450,0.04577,0.03936,0.0151,0.0191,1.0000 6.750,0.6536,0.04975,0.04374,0.0171,0.0207,1.0000 7.000,0.6600,0.05372,0.04796,0.0187,0.0222,1.0000 7.250,0.6710,0.06096,0.05568,0.0207,0.0499,1.0000 7.500,0.6733,0.06498,0.05995,0.0213,0.0492,1.0000 7.750,0.6737,0.06899,0.06411,0.0216,0.0481,1.0000 8.000,0.6727,0.07298,0.06820,0.0215,0.0471,1.0000 8.250,0.6717,0.07689,0.07216,0.0215,0.0460,1.0000 9.250,0.5246,0.08582,0.08130,0.0166,0.0487,1.0000 9.500,0.5186,0.09064,0.08609,0.0148,0.0483,1.0000