XFOIL Version 6.96 Calculated polar for: CLARK X 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 ------ -------- --------- --------- -------- -------- -------- -14.500 -1.0427 0.03696 0.03359 -0.0878 1.0000 0.0159 -14.250 -1.0539 0.03397 0.03044 -0.0876 1.0000 0.0162 -14.000 -1.0577 0.03208 0.02841 -0.0857 1.0000 0.0167 -13.750 -1.0560 0.03049 0.02667 -0.0837 1.0000 0.0173 -13.500 -1.0528 0.02910 0.02513 -0.0814 1.0000 0.0178 -13.250 -1.0470 0.02797 0.02391 -0.0791 1.0000 0.0184 -13.000 -1.0380 0.02715 0.02304 -0.0769 1.0000 0.0190 -12.750 -1.0201 0.02635 0.02215 -0.0762 0.9990 0.0198 -12.500 -0.9929 0.02539 0.02107 -0.0774 0.9967 0.0208 -12.250 -0.9654 0.02437 0.01988 -0.0787 0.9945 0.0217 -12.000 -0.9385 0.02343 0.01876 -0.0796 0.9918 0.0224 -11.750 -0.9112 0.02262 0.01790 -0.0805 0.9889 0.0233 -11.500 -0.8811 0.02209 0.01730 -0.0817 0.9866 0.0242 -11.250 -0.8502 0.02152 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0.2095 0.00885 0.00184 -0.0827 0.7153 0.1540 -1.250 0.2365 0.00872 0.00177 -0.0825 0.7046 0.1801 -1.000 0.2630 0.00854 0.00174 -0.0823 0.6947 0.2358 -0.750 0.2900 0.00844 0.00172 -0.0821 0.6848 0.2752 -0.500 0.3173 0.00839 0.00170 -0.0820 0.6750 0.3007 -0.250 0.3444 0.00833 0.00168 -0.0818 0.6654 0.3266 0.000 0.3713 0.00824 0.00167 -0.0816 0.6549 0.3611 0.250 0.3978 0.00810 0.00168 -0.0814 0.6448 0.4152 0.500 0.4230 0.00783 0.00171 -0.0810 0.6342 0.5224 0.750 0.4464 0.00746 0.00176 -0.0801 0.6231 0.6623 1.000 0.4673 0.00709 0.00186 -0.0784 0.6118 0.8101 1.250 0.4916 0.00701 0.00196 -0.0772 0.6001 0.8995 1.500 0.5240 0.00710 0.00203 -0.0779 0.5833 0.9419 1.750 0.5608 0.00727 0.00209 -0.0798 0.5610 0.9712 2.000 0.5969 0.00743 0.00215 -0.0817 0.5414 0.9861 2.250 0.6333 0.00757 0.00222 -0.0836 0.5266 0.9957 2.500 0.6648 0.00772 0.00229 -0.0845 0.5108 1.0000 2.750 0.6885 0.00788 0.00237 -0.0836 0.4950 1.0000 3.000 0.7122 0.00805 0.00247 -0.0828 0.4795 1.0000 3.250 0.7360 0.00822 0.00258 -0.0820 0.4648 1.0000 3.500 0.7599 0.00840 0.00269 -0.0812 0.4498 1.0000 3.750 0.7839 0.00859 0.00283 -0.0804 0.4343 1.0000 4.000 0.8079 0.00880 0.00297 -0.0797 0.4185 1.0000 4.250 0.8318 0.00902 0.00312 -0.0790 0.4015 1.0000 4.500 0.8557 0.00926 0.00330 -0.0782 0.3840 1.0000 4.750 0.8796 0.00951 0.00348 -0.0775 0.3678 1.0000 5.000 0.9037 0.00975 0.00368 -0.0769 0.3533 1.0000 5.250 0.9278 0.01000 0.00389 -0.0762 0.3394 1.0000 5.500 0.9518 0.01027 0.00411 -0.0755 0.3260 1.0000 5.750 0.9752 0.01057 0.00435 -0.0748 0.3084 1.0000 6.000 0.9979 0.01092 0.00461 -0.0740 0.2875 1.0000 6.250 1.0199 0.01133 0.00491 -0.0730 0.2642 1.0000 6.500 1.0413 0.01179 0.00524 -0.0720 0.2383 1.0000 6.750 1.0629 0.01223 0.00557 -0.0711 0.2156 1.0000 7.000 1.0847 0.01264 0.00591 -0.0702 0.1978 1.0000 7.250 1.1059 0.01310 0.00628 -0.0692 0.1800 1.0000 7.500 1.1268 0.01357 0.00667 -0.0681 0.1628 1.0000 7.750 1.1477 0.01403 0.00707 -0.0671 0.1466 1.0000 8.000 1.1665 0.01463 0.00754 -0.0658 0.1218 1.0000 8.250 1.1798 0.01560 0.00825 -0.0637 0.0815 1.0000 8.500 1.1929 0.01655 0.00903 -0.0616 0.0514 1.0000 8.750 1.2061 0.01736 0.00974 -0.0594 0.0357 1.0000 9.000 1.2216 0.01799 0.01036 -0.0575 0.0294 1.0000 9.250 1.2377 0.01860 0.01099 -0.0558 0.0254 1.0000 9.500 1.2533 0.01925 0.01166 -0.0541 0.0223 1.0000 9.750 1.2692 0.01988 0.01234 -0.0525 0.0204 1.0000 10.000 1.2847 0.02055 0.01304 -0.0509 0.0187 1.0000 10.250 1.2986 0.02132 0.01384 -0.0492 0.0172 1.0000 10.500 1.3125 0.02211 0.01468 -0.0475 0.0162 1.0000 10.750 1.3266 0.02289 0.01553 -0.0460 0.0152 1.0000 11.000 1.3397 0.02376 0.01646 -0.0444 0.0144 1.0000 11.250 1.3514 0.02475 0.01749 -0.0427 0.0137 1.0000 11.500 1.3610 0.02593 0.01872 -0.0410 0.0130 1.0000 11.750 1.3706 0.02713 0.02000 -0.0393 0.0126 1.0000 12.000 1.3810 0.02831 0.02127 -0.0379 0.0122 1.0000 12.250 1.3902 0.02961 0.02265 -0.0365 0.0118 1.0000 12.500 1.3988 0.03101 0.02414 -0.0352 0.0113 1.0000 12.750 1.4066 0.03251 0.02572 -0.0339 0.0109 1.0000 13.000 1.4136 0.03414 0.02741 -0.0328 0.0105 1.0000 13.250 1.4186 0.03599 0.02934 -0.0316 0.0102 1.0000 13.500 1.4207 0.03819 0.03162 -0.0306 0.0099 1.0000 13.750 1.4206 0.04068 0.03420 -0.0296 0.0096 1.0000 14.000 1.4239 0.04290 0.03653 -0.0289 0.0095 1.0000 14.250 1.4256 0.04537 0.03911 -0.0283 0.0093 1.0000 14.500 1.4262 0.04803 0.04188 -0.0278 0.0091 1.0000 14.750 1.4258 0.05091 0.04487 -0.0276 0.0089 1.0000 15.000 1.4242 0.05402 0.04810 -0.0275 0.0088 1.0000 15.250 1.4221 0.05732 0.05150 -0.0276 0.0086 1.0000 15.500 1.4188 0.06084 0.05514 -0.0279 0.0085 1.0000 15.750 1.4148 0.06459 0.05899 -0.0284 0.0084 1.0000 16.000 1.4101 0.06852 0.06303 -0.0291 0.0082 1.0000 16.250 1.4045 0.07268 0.06730 -0.0299 0.0081 1.0000 16.500 1.3982 0.07702 0.07175 -0.0309 0.0080 1.0000 16.750 1.3909 0.08161 0.07645 -0.0322 0.0079 1.0000 17.000 1.3834 0.08632 0.08127 -0.0335 0.0078 1.0000 17.250 1.3750 0.09123 0.08629 -0.0350 0.0077 1.0000 17.500 1.3659 0.09633 0.09149 -0.0367 0.0077 1.0000 17.750 1.3565 0.10154 0.09682 -0.0385 0.0076 1.0000 18.000 1.3468 0.10688 0.10226 -0.0405 0.0075 1.0000 18.250 1.3368 0.11231 0.10778 -0.0425 0.0074 1.0000 18.500 1.3268 0.11777 0.11334 -0.0447 0.0073 1.0000