XFOIL Version 6.96 Calculated polar for: NACA M2 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.7111 0.09164 0.08465 -0.0031 1.0000 0.0559 -9.250 -0.7256 0.08452 0.07754 -0.0087 1.0000 0.0549 -9.000 -0.7416 0.07871 0.07167 -0.0114 1.0000 0.0542 -8.750 -0.7501 0.07370 0.06654 -0.0129 1.0000 0.0546 -8.500 -0.7547 0.06900 0.06166 -0.0137 1.0000 0.0554 -8.250 -0.7566 0.06431 0.05672 -0.0141 1.0000 0.0562 -8.000 -0.7555 0.05958 0.05165 -0.0141 1.0000 0.0569 -7.750 -0.7508 0.05493 0.04660 -0.0137 1.0000 0.0575 -7.500 -0.7424 0.05061 0.04180 -0.0131 1.0000 0.0590 -7.250 -0.7319 0.04644 0.03692 -0.0121 1.0000 0.0620 -7.000 -0.7161 0.04336 0.03351 -0.0114 1.0000 0.0649 -6.750 -0.6972 0.04065 0.03045 -0.0107 1.0000 0.0671 -6.500 -0.6769 0.03804 0.02743 -0.0099 1.0000 0.0703 -6.250 -0.6553 0.03560 0.02428 -0.0089 1.0000 0.0757 -6.000 -0.6324 0.03354 0.02213 -0.0084 1.0000 0.0790 -5.750 -0.6079 0.03156 0.01988 -0.0078 1.0000 0.0823 -5.500 -0.5821 0.02970 0.01768 -0.0071 1.0000 0.0864 -5.250 -0.5565 0.02811 0.01589 -0.0064 1.0000 0.0916 -5.000 -0.5316 0.02699 0.01460 -0.0058 1.0000 0.1013 -4.750 -0.5065 0.02564 0.01325 -0.0051 1.0000 0.1097 -4.500 -0.4813 0.02436 0.01185 -0.0043 1.0000 0.1202 -4.250 -0.4574 0.02316 0.01058 -0.0035 1.0000 0.1349 -4.000 -0.4344 0.02206 0.00949 -0.0028 1.0000 0.1540 -3.750 -0.4118 0.02101 0.00856 -0.0022 1.0000 0.1867 -3.500 -0.3920 0.01963 0.00762 -0.0015 1.0000 0.2414 -3.250 -0.3796 0.01762 0.00712 0.0010 1.0000 0.4732 -3.000 -0.3638 0.01685 0.00719 0.0051 1.0000 0.6700 -2.750 -0.3393 0.01672 0.00724 0.0078 1.0000 0.7763 -2.500 -0.3042 0.01683 0.00726 0.0082 1.0000 0.8462 -2.250 -0.2662 0.01695 0.00718 0.0073 1.0000 0.8949 -2.000 -0.2200 0.01705 0.00706 0.0044 1.0000 0.9407 -1.750 -0.1459 0.01704 0.00673 -0.0045 1.0000 0.9794 -1.500 -0.0903 0.01677 0.00628 -0.0107 1.0000 1.0000 -1.250 -0.0740 0.01653 0.00596 -0.0093 1.0000 1.0000 -1.000 -0.0582 0.01635 0.00572 -0.0078 1.0000 1.0000 -0.750 -0.0429 0.01620 0.00554 -0.0061 1.0000 1.0000 -0.500 -0.0283 0.01611 0.00542 -0.0041 1.0000 1.0000 -0.250 -0.0141 0.01605 0.00534 -0.0021 1.0000 1.0000 0.000 0.0000 0.01603 0.00532 0.0000 1.0000 1.0000 0.250 0.0141 0.01605 0.00534 0.0021 1.0000 1.0000 0.500 0.0283 0.01611 0.00542 0.0041 1.0000 1.0000 0.750 0.0430 0.01620 0.00554 0.0061 1.0000 1.0000 1.000 0.0582 0.01634 0.00572 0.0078 1.0000 1.0000 1.250 0.0740 0.01653 0.00596 0.0093 1.0000 1.0000 1.500 0.0903 0.01677 0.00628 0.0107 1.0000 1.0000 1.750 0.1459 0.01704 0.00673 0.0045 0.9794 1.0000 2.000 0.2199 0.01705 0.00705 -0.0044 0.9408 1.0000 2.250 0.2662 0.01694 0.00718 -0.0073 0.8949 1.0000 2.500 0.3042 0.01683 0.00726 -0.0082 0.8462 1.0000 2.750 0.3393 0.01672 0.00723 -0.0078 0.7764 1.0000 3.000 0.3638 0.01685 0.00719 -0.0051 0.6701 1.0000 3.250 0.3796 0.01762 0.00712 -0.0010 0.4734 1.0000 3.500 0.3920 0.01962 0.00761 0.0015 0.2414 1.0000 3.750 0.4118 0.02101 0.00855 0.0022 0.1866 1.0000 4.000 0.4344 0.02206 0.00949 0.0028 0.1539 1.0000 4.250 0.4574 0.02316 0.01058 0.0035 0.1349 1.0000 4.500 0.4813 0.02436 0.01185 0.0043 0.1202 1.0000 4.750 0.5065 0.02564 0.01325 0.0051 0.1097 1.0000 5.000 0.5317 0.02699 0.01460 0.0058 0.1013 1.0000 5.250 0.5565 0.02811 0.01588 0.0064 0.0916 1.0000 5.500 0.5821 0.02970 0.01768 0.0071 0.0864 1.0000 5.750 0.6079 0.03156 0.01988 0.0078 0.0823 1.0000 6.000 0.6324 0.03354 0.02213 0.0084 0.0790 1.0000 6.250 0.6553 0.03560 0.02429 0.0089 0.0757 1.0000 6.500 0.6769 0.03804 0.02743 0.0099 0.0703 1.0000 6.750 0.6972 0.04066 0.03046 0.0107 0.0671 1.0000 7.000 0.7162 0.04337 0.03352 0.0114 0.0649 1.0000 7.250 0.7320 0.04644 0.03693 0.0121 0.0620 1.0000 7.500 0.7425 0.05062 0.04181 0.0130 0.0590 1.0000 7.750 0.7509 0.05494 0.04661 0.0137 0.0575 1.0000 8.000 0.7556 0.05959 0.05167 0.0141 0.0569 1.0000 8.250 0.7568 0.06433 0.05674 0.0141 0.0562 1.0000 8.500 0.7550 0.06902 0.06168 0.0137 0.0554 1.0000 8.750 0.7505 0.07368 0.06652 0.0129 0.0545 1.0000 9.000 0.7423 0.07868 0.07164 0.0114 0.0542 1.0000 9.250 0.7261 0.08454 0.07757 0.0086 0.0548 1.0000 9.500 0.7117 0.09166 0.08467 0.0030 0.0558 1.0000