XFOIL Version 6.96 Calculated polar for: NACA-M1 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.7796 0.08053 0.07847 0.0112 1.0000 0.0050 -9.000 -0.7938 0.07176 0.06969 0.0017 1.0000 0.0049 -8.750 -0.8077 0.06146 0.05921 -0.0047 1.0000 0.0048 -8.500 -0.8768 0.03035 0.02663 -0.0067 1.0000 0.0046 -8.250 -0.8668 0.02480 0.02033 -0.0054 1.0000 0.0049 -8.000 -0.8480 0.02198 0.01705 -0.0045 1.0000 0.0051 -7.750 -0.8265 0.02002 0.01469 -0.0039 1.0000 0.0054 -7.500 -0.8033 0.01855 0.01295 -0.0033 1.0000 0.0056 -7.250 -0.7807 0.01687 0.01102 -0.0027 1.0000 0.0061 -7.000 -0.7558 0.01610 0.01013 -0.0025 1.0000 0.0066 -6.750 -0.7302 0.01551 0.00946 -0.0023 1.0000 0.0074 -6.500 -0.7049 0.01473 0.00854 -0.0019 1.0000 0.0081 -6.250 -0.6795 0.01393 0.00760 -0.0016 1.0000 0.0087 -6.000 -0.6545 0.01295 0.00650 -0.0011 1.0000 0.0101 -5.750 -0.6282 0.01253 0.00605 -0.0010 1.0000 0.0117 -5.500 -0.6015 0.01225 0.00574 -0.0008 1.0000 0.0137 -5.250 -0.5750 0.01181 0.00530 -0.0007 1.0000 0.0170 -5.000 -0.5480 0.01161 0.00507 -0.0006 1.0000 0.0210 -4.750 -0.5207 0.01153 0.00494 -0.0005 1.0000 0.0243 -4.500 -0.4933 0.01149 0.00485 -0.0004 1.0000 0.0255 -4.250 -0.4673 0.01095 0.00425 -0.0002 1.0000 0.0276 -4.000 -0.4409 0.01053 0.00381 0.0000 1.0000 0.0298 -3.750 -0.4143 0.01024 0.00348 0.0001 1.0000 0.0315 -3.500 -0.3876 0.00995 0.00315 0.0003 1.0000 0.0327 -3.250 -0.3610 0.00968 0.00284 0.0005 1.0000 0.0336 -3.000 -0.3343 0.00941 0.00253 0.0007 1.0000 0.0339 -2.750 -0.3078 0.00917 0.00225 0.0010 1.0000 0.0342 -2.500 -0.2813 0.00897 0.00201 0.0013 1.0000 0.0348 -2.250 -0.2550 0.00880 0.00182 0.0016 1.0000 0.0358 -2.000 -0.2290 0.00864 0.00165 0.0020 1.0000 0.0380 -1.750 -0.2033 0.00843 0.00151 0.0024 1.0000 0.0494 -1.500 -0.1784 0.00797 0.00138 0.0027 1.0000 0.1291 -1.250 -0.1493 0.00745 0.00126 0.0020 0.9976 0.2367 -1.000 -0.1161 0.00685 0.00116 0.0004 0.9922 0.3717 -0.750 -0.0831 0.00627 0.00109 -0.0012 0.9842 0.5097 -0.500 -0.0471 0.00572 0.00105 -0.0031 0.9616 0.6464 -0.250 -0.0190 0.00532 0.00105 -0.0028 0.9125 0.7648 0.000 0.0000 0.00517 0.00106 0.0000 0.8526 0.8537 0.250 0.0189 0.00531 0.00105 0.0028 0.7647 0.9142 0.500 0.0473 0.00572 0.00105 0.0031 0.6460 0.9624 0.750 0.0831 0.00627 0.00109 0.0012 0.5089 0.9842 1.000 0.1161 0.00686 0.00116 -0.0004 0.3710 0.9921 1.250 0.1493 0.00746 0.00126 -0.0020 0.2341 0.9976 1.500 0.1784 0.00797 0.00138 -0.0027 0.1293 1.0000 1.750 0.2034 0.00843 0.00151 -0.0024 0.0495 1.0000 2.000 0.2290 0.00864 0.00165 -0.0020 0.0380 1.0000 2.250 0.2551 0.00880 0.00182 -0.0016 0.0357 1.0000 2.500 0.2814 0.00897 0.00202 -0.0013 0.0348 1.0000 2.750 0.3078 0.00918 0.00225 -0.0010 0.0342 1.0000 3.000 0.3344 0.00941 0.00253 -0.0007 0.0339 1.0000 3.250 0.3610 0.00968 0.00284 -0.0005 0.0336 1.0000 3.500 0.3877 0.00995 0.00315 -0.0003 0.0326 1.0000 3.750 0.4143 0.01024 0.00349 -0.0001 0.0314 1.0000 4.000 0.4410 0.01054 0.00381 0.0000 0.0298 1.0000 4.250 0.4673 0.01095 0.00425 0.0002 0.0276 1.0000 4.500 0.4933 0.01150 0.00485 0.0004 0.0255 1.0000 4.750 0.5207 0.01153 0.00494 0.0005 0.0243 1.0000 5.000 0.5480 0.01161 0.00507 0.0005 0.0210 1.0000 5.250 0.5751 0.01181 0.00529 0.0006 0.0170 1.0000 5.500 0.6015 0.01225 0.00574 0.0008 0.0137 1.0000 5.750 0.6282 0.01253 0.00605 0.0010 0.0117 1.0000 6.000 0.6546 0.01295 0.00649 0.0011 0.0101 1.0000 6.250 0.6795 0.01393 0.00760 0.0016 0.0087 1.0000 6.500 0.7049 0.01472 0.00854 0.0019 0.0081 1.0000 6.750 0.7302 0.01550 0.00945 0.0023 0.0074 1.0000 7.000 0.7557 0.01610 0.01014 0.0025 0.0066 1.0000 7.250 0.7807 0.01688 0.01103 0.0027 0.0061 1.0000 7.500 0.8033 0.01856 0.01296 0.0033 0.0056 1.0000 7.750 0.8264 0.02002 0.01470 0.0039 0.0054 1.0000 8.000 0.8480 0.02198 0.01705 0.0045 0.0051 1.0000 8.250 0.8667 0.02480 0.02034 0.0054 0.0049 1.0000 8.500 0.8768 0.03033 0.02661 0.0068 0.0046 1.0000 8.750 0.8076 0.06153 0.05928 0.0047 0.0048 1.0000 9.000 0.7938 0.07184 0.06976 -0.0018 0.0049 1.0000 9.250 0.7798 0.08059 0.07854 -0.0113 0.0050 1.0000