XFOIL Version 6.96 Calculated polar for: FX 66-17AII-182 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.500 -0.3100 0.08150 0.07858 -0.0995 0.8228 0.0156 -13.250 -0.3412 0.07161 0.06844 -0.1055 0.7917 0.0152 -13.000 -0.3672 0.06452 0.06112 -0.1097 0.7654 0.0147 -12.750 -0.4037 0.05705 0.05337 -0.1137 0.7477 0.0147 -12.500 -0.4295 0.05190 0.04798 -0.1157 0.7312 0.0144 -12.250 -0.4522 0.04759 0.04342 -0.1166 0.7168 0.0145 -12.000 -0.4763 0.04334 0.03890 -0.1167 0.7047 0.0142 -11.750 -0.4907 0.04041 0.03573 -0.1162 0.6935 0.0145 -11.500 -0.5064 0.03726 0.03233 -0.1152 0.6846 0.0143 -11.250 -0.5179 0.03464 0.02945 -0.1136 0.6764 0.0143 -11.000 -0.5249 0.03252 0.02710 -0.1116 0.6691 0.0145 -10.750 -0.5294 0.03066 0.02501 -0.1090 0.6624 0.0146 -10.500 -0.5294 0.02927 0.02341 -0.1062 0.6566 0.0148 -10.250 -0.5238 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0.3351 0.01108 0.00453 -0.0825 0.5462 0.6176 -0.500 0.3632 0.01111 0.00456 -0.0827 0.5443 0.6203 -0.250 0.3913 0.01115 0.00458 -0.0828 0.5423 0.6234 0.000 0.4194 0.01121 0.00459 -0.0830 0.5403 0.6267 0.250 0.4476 0.01126 0.00458 -0.0832 0.5384 0.6299 0.500 0.4759 0.01128 0.00460 -0.0834 0.5366 0.6326 0.750 0.5044 0.01138 0.00468 -0.0837 0.5349 0.6355 1.000 0.5328 0.01152 0.00480 -0.0840 0.5331 0.6382 1.250 0.5603 0.01155 0.00484 -0.0841 0.5315 0.6407 1.500 0.5879 0.01160 0.00490 -0.0842 0.5297 0.6431 1.750 0.6156 0.01165 0.00494 -0.0843 0.5278 0.6454 2.000 0.6433 0.01165 0.00497 -0.0845 0.5257 0.6477 2.250 0.6712 0.01168 0.00502 -0.0847 0.5238 0.6499 2.500 0.6993 0.01174 0.00507 -0.0849 0.5221 0.6523 2.750 0.7276 0.01183 0.00514 -0.0852 0.5203 0.6549 3.000 0.7563 0.01203 0.00531 -0.0856 0.5183 0.6578 3.250 0.7829 0.01208 0.00540 -0.0856 0.5165 0.6603 3.500 0.8095 0.01210 0.00548 -0.0855 0.5145 0.6625 3.750 0.8364 0.01214 0.00558 -0.0856 0.5124 0.6648 4.000 0.8636 0.01220 0.00568 -0.0856 0.5104 0.6673 4.250 0.8910 0.01227 0.00578 -0.0858 0.5085 0.6701 4.500 0.9188 0.01236 0.00588 -0.0860 0.5068 0.6729 4.750 0.9469 0.01247 0.00598 -0.0863 0.5051 0.6756 5.000 0.9752 0.01265 0.00618 -0.0867 0.5033 0.6786 5.250 1.0010 0.01275 0.00637 -0.0865 0.5015 0.6814 5.500 1.0264 0.01282 0.00654 -0.0863 0.4994 0.6848 5.750 1.0520 0.01287 0.00666 -0.0861 0.4968 0.6882 6.000 1.0781 0.01286 0.00667 -0.0860 0.4935 0.6914 6.250 1.1050 0.01281 0.00663 -0.0860 0.4903 0.6943 6.500 1.1317 0.01290 0.00676 -0.0860 0.4870 0.6974 6.750 1.1545 0.01290 0.00688 -0.0853 0.4837 0.7008 7.000 1.1789 0.01291 0.00697 -0.0848 0.4803 0.7045 7.250 1.2043 0.01292 0.00702 -0.0846 0.4770 0.7082 7.500 1.2302 0.01294 0.00707 -0.0844 0.4735 0.7121 7.750 1.2518 0.01297 0.00722 -0.0835 0.4694 0.7167 8.000 1.2736 0.01295 0.00729 -0.0825 0.4645 0.7217 8.250 1.2965 0.01293 0.00733 -0.0818 0.4599 0.7266 8.500 1.3156 0.01292 0.00743 -0.0803 0.4532 0.7321 8.750 1.3324 0.01288 0.00738 -0.0784 0.4432 0.7385 9.000 1.3460 0.01287 0.00748 -0.0759 0.4304 0.7455 9.250 1.3593 0.01297 0.00766 -0.0734 0.4185 0.7543 9.500 1.3715 0.01313 0.00791 -0.0707 0.4084 0.7653 9.750 1.3819 0.01337 0.00823 -0.0678 0.3975 0.7813 10.000 1.3875 0.01370 0.00866 -0.0641 0.3811 0.8105 10.250 1.4204 0.01481 0.00989 -0.0678 0.3348 1.0000 10.500 1.4065 0.01653 0.01140 -0.0626 0.2980 1.0000 10.750 1.3867 0.01910 0.01378 -0.0581 0.2593 1.0000 11.000 1.3661 0.02248 0.01703 -0.0550 0.2267 1.0000 11.250 1.3439 0.02660 0.02102 -0.0529 0.1960 1.0000 11.500 1.3264 0.03058 0.02491 -0.0514 0.1704 1.0000 11.750 1.3072 0.03478 0.02902 -0.0500 0.1461 1.0000 12.000 1.2885 0.03896 0.03310 -0.0487 0.1233 1.0000 12.250 1.2696 0.04319 0.03723 -0.0475 0.1007 1.0000 12.500 1.2561 0.04706 0.04101 -0.0466 0.0805 1.0000 12.750 1.2412 0.05116 0.04500 -0.0457 0.0601 1.0000 13.000 1.2342 0.05458 0.04837 -0.0452 0.0468 1.0000 13.250 1.2262 0.05814 0.05186 -0.0447 0.0348 1.0000 13.500 1.2241 0.06115 0.05486 -0.0444 0.0288 1.0000 13.750 1.2253 0.06388 0.05762 -0.0441 0.0244 1.0000 14.000 1.2255 0.06673 0.06048 -0.0439 0.0213 1.0000 14.250 1.2277 0.06938 0.06316 -0.0438 0.0194 1.0000 14.500 1.2288 0.07219 0.06600 -0.0437 0.0181 1.0000 14.750 1.2307 0.07492 0.06878 -0.0436 0.0168 1.0000 15.000 1.2324 0.07774 0.07167 -0.0437 0.0163 1.0000 15.250 1.2326 0.08070 0.07469 -0.0436 0.0156 1.0000 15.500 1.2315 0.08388 0.07791 -0.0437 0.0149 1.0000 15.750 1.2302 0.08711 0.08120 -0.0438 0.0145 1.0000