XFOIL Version 6.96 Calculated polar for: NACA M6 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.3372 0.09748 0.09259 -0.0253 1.0000 0.1375 -9.500 -0.3433 0.09411 0.08926 -0.0267 1.0000 0.1432 -9.250 -0.3893 0.09014 0.08540 -0.0326 1.0000 0.1461 -9.000 -0.3606 0.08566 0.08092 -0.0296 1.0000 0.1493 -8.750 -0.3468 0.08262 0.07789 -0.0285 1.0000 0.1532 -8.500 -0.3543 0.07894 0.07426 -0.0296 1.0000 0.1585 -8.250 -0.4203 0.07405 0.06948 -0.0353 1.0000 0.1621 -8.000 -0.4734 0.07184 0.06729 -0.0320 1.0000 0.1627 -7.750 -0.3858 0.06641 0.06192 -0.0323 1.0000 0.1694 -7.500 -0.4044 0.06299 0.05856 -0.0316 1.0000 0.1737 -7.250 -0.4518 0.06088 0.05655 -0.0274 1.0000 0.1772 -7.000 -0.5098 0.06088 0.05657 -0.0199 1.0000 0.1787 -6.750 -0.5536 0.06128 0.05696 -0.0124 1.0000 0.1791 -6.500 -0.5765 0.06382 0.05910 -0.0105 1.0000 0.1819 -6.250 -0.5840 0.06222 0.05759 -0.0061 1.0000 0.1840 -6.000 -0.5969 0.06102 0.05641 -0.0013 1.0000 0.1869 -5.750 -0.5977 0.05852 0.05371 -0.0009 0.9940 0.1986 -5.500 -0.5711 0.05529 0.05029 -0.0037 0.9837 0.2146 -5.250 -0.5527 0.04282 0.03608 -0.0042 0.9712 0.1131 -5.000 -0.5303 0.03805 0.03042 -0.0031 0.9604 0.0997 -4.750 -0.4947 0.03465 0.02673 -0.0051 0.9534 0.0967 -4.500 -0.4633 0.03194 0.02358 -0.0058 0.9436 0.0941 -4.250 -0.4245 0.02956 0.02074 -0.0076 0.9364 0.0927 -4.000 -0.3850 0.02780 0.01864 -0.0096 0.9280 0.0937 -3.750 -0.3320 0.02614 0.01671 -0.0142 0.9238 0.0975 -3.500 -0.2946 0.02491 0.01524 -0.0158 0.9137 0.0997 -3.250 -0.2388 0.02305 0.01339 -0.0210 0.9091 0.1040 -3.000 -0.2003 0.02207 0.01245 -0.0229 0.8994 0.1105 -2.750 -0.1545 0.02089 0.01138 -0.0262 0.8927 0.1242 -2.500 -0.1253 0.02005 0.01064 -0.0262 0.8816 0.1437 -2.250 0.1733 0.01831 0.01184 -0.0713 0.9093 0.9840 -2.000 0.2465 0.01740 0.01067 -0.0806 0.8973 1.0000 -1.750 0.2748 0.01727 0.01037 -0.0810 0.8805 1.0000 -1.500 0.2990 0.01722 0.01017 -0.0806 0.8643 1.0000 -1.250 0.3201 0.01722 0.01004 -0.0795 0.8491 1.0000 -1.000 0.3400 0.01725 0.00995 -0.0781 0.8349 1.0000 -0.750 0.3599 0.01729 0.00987 -0.0766 0.8220 1.0000 -0.500 0.3795 0.01733 0.00980 -0.0751 0.8095 1.0000 -0.250 0.3984 0.01742 0.00982 -0.0736 0.7964 1.0000 0.000 0.4178 0.01752 0.00984 -0.0721 0.7845 1.0000 0.250 0.4384 0.01758 0.00979 -0.0706 0.7743 1.0000 0.500 0.4578 0.01771 0.00988 -0.0691 0.7621 1.0000 0.750 0.4775 0.01785 0.00998 -0.0677 0.7509 1.0000 1.000 0.4989 0.01792 0.00996 -0.0663 0.7417 1.0000 1.250 0.5182 0.01812 0.01015 -0.0649 0.7297 1.0000 1.500 0.5386 0.01829 0.01029 -0.0635 0.7196 1.0000 1.750 0.5599 0.01840 0.01035 -0.0621 0.7098 1.0000 2.000 0.5796 0.01864 0.01061 -0.0607 0.6986 1.0000 2.250 0.6013 0.01877 0.01067 -0.0594 0.6896 1.0000 2.500 0.6214 0.01897 0.01089 -0.0580 0.6784 1.0000 2.750 0.6416 0.01919 0.01113 -0.0566 0.6677 1.0000 3.000 0.6641 0.01924 0.01111 -0.0552 0.6585 1.0000 3.250 0.6833 0.01947 0.01140 -0.0536 0.6462 1.0000 3.500 0.7039 0.01964 0.01158 -0.0522 0.6352 1.0000 3.750 0.7266 0.01966 0.01156 -0.0508 0.6256 1.0000 4.000 0.7458 0.01991 0.01189 -0.0492 0.6133 1.0000 4.250 0.7666 0.02009 0.01209 -0.0478 0.6024 1.0000 4.500 0.7897 0.02011 0.01208 -0.0465 0.5927 1.0000 4.750 0.8087 0.02041 0.01248 -0.0449 0.5806 1.0000 5.000 0.8294 0.02059 0.01271 -0.0434 0.5695 1.0000 5.250 0.8530 0.02061 0.01271 -0.0422 0.5598 1.0000 5.500 0.8720 0.02084 0.01304 -0.0405 0.5466 1.0000 5.750 0.8920 0.02097 0.01322 -0.0389 0.5333 1.0000 6.000 0.9126 0.02097 0.01325 -0.0371 0.5193 1.0000 6.250 0.9332 0.02090 0.01320 -0.0354 0.5040 1.0000 6.500 0.9533 0.02084 0.01315 -0.0335 0.4877 1.0000 6.750 0.9724 0.02071 0.01302 -0.0314 0.4693 1.0000 7.000 0.9913 0.02057 0.01284 -0.0293 0.4496 1.0000 7.250 1.0091 0.02054 0.01280 -0.0272 0.4295 1.0000 7.500 1.0244 0.02068 0.01303 -0.0247 0.4077 1.0000 7.750 1.0401 0.02085 0.01320 -0.0224 0.3858 1.0000 8.000 1.0536 0.02112 0.01352 -0.0197 0.3612 1.0000 8.250 1.0652 0.02149 0.01387 -0.0168 0.3330 1.0000 8.500 1.0731 0.02205 0.01439 -0.0135 0.2972 1.0000 8.750 1.0747 0.02299 0.01513 -0.0093 0.2507 1.0000 9.000 1.0671 0.02459 0.01631 -0.0040 0.2002 1.0000 9.250 1.0584 0.02639 0.01777 0.0013 0.1638 1.0000 9.500 1.0520 0.02801 0.01915 0.0062 0.1424 1.0000 9.750 1.0465 0.02938 0.02040 0.0110 0.1289 1.0000 10.000 1.0442 0.03071 0.02168 0.0153 0.1187 1.0000 10.250 1.0452 0.03218 0.02302 0.0187 0.1105 1.0000 10.500 1.0505 0.03355 0.02436 0.0215 0.1030 1.0000 10.750 1.0637 0.03508 0.02584 0.0233 0.0968 1.0000 11.000 1.0765 0.03652 0.02725 0.0251 0.0908 1.0000 11.250 1.1009 0.03840 0.02910 0.0255 0.0853 1.0000 11.500 1.1156 0.04003 0.03089 0.0270 0.0814 1.0000 11.750 1.1624 0.04308 0.03375 0.0238 0.0756 1.0000 12.000 1.1584 0.04446 0.03543 0.0279 0.0738 1.0000 12.250 1.1628 0.04643 0.03767 0.0304 0.0719 1.0000 12.500 1.1686 0.04867 0.04014 0.0325 0.0703 1.0000 12.750 1.1744 0.05091 0.04254 0.0344 0.0685 1.0000 13.000 1.1794 0.05319 0.04492 0.0361 0.0668 1.0000 13.250 1.1936 0.05728 0.04906 0.0363 0.0646 1.0000 13.500 1.1776 0.05970 0.05176 0.0395 0.0643 1.0000 13.750 1.1584 0.06248 0.05482 0.0421 0.0639 1.0000 14.000 1.1430 0.06587 0.05846 0.0437 0.0638 1.0000 14.250 1.1231 0.06975 0.06259 0.0447 0.0637 1.0000 14.500 1.1026 0.07408 0.06716 0.0450 0.0638 1.0000 14.750 1.0815 0.07888 0.07216 0.0446 0.0640 1.0000 15.000 1.0559 0.08438 0.07787 0.0435 0.0641 1.0000 15.250 1.0330 0.09031 0.08397 0.0419 0.0644 1.0000 15.500 1.0102 0.09682 0.09061 0.0398 0.0647 1.0000 15.750 0.8392 0.13147 0.12577 0.0169 0.0752 1.0000