XFOIL Version 6.94 Calculated polar for: LOCKHEED C-141 BL958.89 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3370 0.00925 0.00315 -0.0771 0.8892 0.1245 1.000 0.4484 0.00642 0.00277 -0.0748 0.8349 0.9778 1.500 0.5469 0.00654 0.00265 -0.0833 0.7868 1.0000 2.000 0.5919 0.00679 0.00255 -0.0805 0.7157 1.0000 2.500 0.6281 0.00745 0.00263 -0.0760 0.5943 1.0000 3.000 0.6506 0.00900 0.00310 -0.0693 0.3745 1.0000 3.500 0.6865 0.01007 0.00358 -0.0654 0.2658 1.0000 4.000 0.7307 0.01070 0.00399 -0.0630 0.2235 1.0000 4.500 0.7764 0.01132 0.00441 -0.0610 0.1894 1.0000 5.000 0.8226 0.01198 0.00487 -0.0590 0.1453 1.0000 6.000 0.9124 0.01363 0.00617 -0.0548 0.1019 1.0000 6.500 0.9580 0.01439 0.00689 -0.0528 0.0938 1.0000 7.000 1.0034 0.01516 0.00769 -0.0509 0.0879 1.0000 7.500 1.0464 0.01613 0.00864 -0.0486 0.0822 1.0000 8.000 1.0915 0.01687 0.00941 -0.0467 0.0764 1.0000 8.500 1.1349 0.01771 0.01031 -0.0446 0.0704 1.0000 9.000 1.1769 0.01858 0.01123 -0.0423 0.0642 1.0000 9.500 1.2171 0.01939 0.01209 -0.0396 0.0573 1.0000 10.000 1.2574 0.02016 0.01291 -0.0371 0.0497 1.0000 10.500 1.2957 0.02112 0.01389 -0.0343 0.0432 1.0000 11.500 1.3595 0.02395 0.01689 -0.0273 0.0347 1.0000 12.000 1.3831 0.02594 0.01897 -0.0230 0.0321 1.0000 12.500 1.4070 0.02790 0.02108 -0.0191 0.0298 1.0000 13.000 1.4210 0.03064 0.02393 -0.0145 0.0282 1.0000 13.500 1.4376 0.03329 0.02681 -0.0106 0.0268 1.0000 14.000 1.4486 0.03648 0.03017 -0.0069 0.0257 1.0000 14.500 1.4492 0.04083 0.03465 -0.0032 0.0249 1.0000 15.000 1.4509 0.04542 0.03954 -0.0006 0.0242 1.0000 15.500 1.4482 0.05081 0.04525 0.0011 0.0236 1.0000 16.000 1.4397 0.05734 0.05207 0.0015 0.0231 1.0000 16.500 1.4262 0.06524 0.06025 0.0004 0.0227 1.0000 17.000 1.4073 0.07469 0.06999 -0.0025 0.0224 1.0000 17.500 1.3828 0.08594 0.08153 -0.0074 0.0221 1.0000 18.000 1.3517 0.09926 0.09516 -0.0142 0.0219 1.0000 18.500 1.3125 0.11503 0.11125 -0.0231 0.0219 1.0000 19.000 1.2552 0.13581 0.13243 -0.0360 0.0220 1.0000