XFOIL Version 6.96 Calculated polar for: FX 83-W-108 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.3733 0.10780 0.10398 -0.0474 1.0000 0.0232 -10.500 -0.3759 0.10451 0.10074 -0.0475 1.0000 0.0230 -10.250 -0.3869 0.09975 0.09604 -0.0482 1.0000 0.0237 -10.000 -0.3908 0.09598 0.09231 -0.0490 0.9994 0.0236 -9.750 -0.3842 0.08980 0.08614 -0.0545 0.9951 0.0235 -9.500 -0.3817 0.08290 0.07925 -0.0606 0.9899 0.0233 -9.250 -0.3854 0.07451 0.07088 -0.0682 0.9823 0.0232 -9.000 -0.4530 0.04149 0.03727 -0.1079 0.9524 0.0222 -8.750 -0.4419 0.03441 0.02950 -0.1158 0.9433 0.0225 -8.500 -0.4234 0.03031 0.02483 -0.1189 0.9358 0.0230 -8.250 -0.3976 0.02719 0.02118 -0.1216 0.9308 0.0236 -8.000 -0.3670 0.02481 0.01831 -0.1240 0.9275 0.0244 -7.750 -0.3426 0.02329 0.01662 -0.1246 0.9209 0.0251 -7.500 -0.3126 0.02239 0.01564 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2.500 0.7967 0.01081 0.00469 -0.1285 0.7271 1.0000 2.750 0.8206 0.01091 0.00483 -0.1277 0.7186 1.0000 3.000 0.8474 0.01095 0.00482 -0.1272 0.7096 1.0000 3.250 0.8715 0.01100 0.00485 -0.1262 0.6975 1.0000 3.500 0.8950 0.01104 0.00489 -0.1251 0.6829 1.0000 3.750 0.9185 0.01109 0.00491 -0.1239 0.6663 1.0000 4.000 0.9415 0.01117 0.00496 -0.1227 0.6492 1.0000 4.250 0.9643 0.01129 0.00507 -0.1215 0.6318 1.0000 4.500 0.9866 0.01143 0.00520 -0.1202 0.6114 1.0000 4.750 1.0078 0.01161 0.00530 -0.1187 0.5846 1.0000 5.000 1.0270 0.01187 0.00543 -0.1168 0.5493 1.0000 5.250 1.0429 0.01229 0.00563 -0.1143 0.5025 1.0000 5.500 1.0528 0.01297 0.00597 -0.1107 0.4403 1.0000 5.750 1.0592 0.01384 0.00647 -0.1068 0.3744 1.0000 6.000 1.0647 0.01480 0.00708 -0.1028 0.3120 1.0000 6.250 1.0709 0.01571 0.00771 -0.0991 0.2601 1.0000 6.500 1.0779 0.01661 0.00836 -0.0955 0.2151 1.0000 6.750 1.0870 0.01748 0.00904 -0.0925 0.1789 1.0000 7.000 1.0983 0.01827 0.00970 -0.0899 0.1511 1.0000 7.250 1.1103 0.01907 0.01038 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12.250 1.3300 0.04179 0.03382 -0.0518 0.0293 1.0000 12.500 1.3359 0.04373 0.03582 -0.0504 0.0283 1.0000 12.750 1.3453 0.04531 0.03755 -0.0492 0.0274 1.0000 13.000 1.3532 0.04711 0.03949 -0.0480 0.0266 1.0000 13.250 1.3605 0.04896 0.04148 -0.0469 0.0258 1.0000 13.500 1.3670 0.05093 0.04357 -0.0458 0.0252 1.0000 13.750 1.3726 0.05300 0.04576 -0.0448 0.0246 1.0000 14.000 1.3775 0.05516 0.04803 -0.0439 0.0241 1.0000 14.250 1.3815 0.05746 0.05045 -0.0431 0.0236 1.0000 14.500 1.3849 0.05988 0.05297 -0.0423 0.0232 1.0000 14.750 1.3871 0.06255 0.05573 -0.0416 0.0228 1.0000 15.000 1.3879 0.06546 0.05880 -0.0410 0.0223 1.0000 15.250 1.3875 0.06849 0.06205 -0.0407 0.0220 1.0000 15.500 1.3848 0.07192 0.06570 -0.0406 0.0215 1.0000 15.750 1.3810 0.07560 0.06960 -0.0407 0.0212 1.0000 16.000 1.3756 0.07958 0.07379 -0.0411 0.0208 1.0000 16.250 1.3682 0.08396 0.07839 -0.0418 0.0204 1.0000 16.500 1.3602 0.08859 0.08323 -0.0429 0.0202 1.0000 16.750 1.3503 0.09371 0.08855 -0.0445 0.0199 1.0000 17.000 1.3390 0.09926 0.09430 -0.0465 0.0197 1.0000 17.250 1.3265 0.10521 0.10047 -0.0490 0.0195 1.0000 17.500 1.3127 0.11168 0.10713 -0.0522 0.0193 1.0000 17.750 1.2963 0.11899 0.11464 -0.0561 0.0192 1.0000 18.000 1.2787 0.12695 0.12280 -0.0607 0.0191 1.0000 18.250 1.2524 0.13745 0.13353 -0.0673 0.0191 1.0000