XFOIL Version 6.96 Calculated polar for: FX 84-W-127 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3320 0.10074 0.09582 -0.0524 1.0000 0.0356 -10.250 -0.3365 0.09672 0.09188 -0.0539 1.0000 0.0357 -10.000 -0.3458 0.09329 0.08855 -0.0543 1.0000 0.0358 -9.750 -0.3450 0.08832 0.08362 -0.0581 0.9893 0.0357 -9.500 -0.3390 0.08219 0.07750 -0.0643 0.9785 0.0356 -9.250 -0.3362 0.07483 0.07014 -0.0722 0.9676 0.0354 -9.000 -0.3395 0.06506 0.06033 -0.0840 0.9542 0.0351 -8.750 -0.3551 0.05654 0.05160 -0.0925 0.9370 0.0347 -8.500 -0.3692 0.05010 0.04482 -0.0960 0.9227 0.0347 -8.250 -0.3781 0.04462 0.03884 -0.0970 0.9108 0.0350 -8.000 -0.3811 0.03981 0.03338 -0.0966 0.9003 0.0357 -7.750 -0.3719 0.03725 0.03048 -0.0958 0.8913 0.0370 -7.500 -0.3527 0.03595 0.02905 -0.0956 0.8849 0.0385 -7.250 -0.3375 0.03398 0.02676 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1.0000 12.250 1.1744 0.05168 0.04279 -0.0293 0.0635 1.0000 12.500 1.1727 0.05460 0.04571 -0.0288 0.0592 1.0000 12.750 1.1755 0.05711 0.04833 -0.0283 0.0554 1.0000 13.000 1.1778 0.05973 0.05104 -0.0280 0.0520 1.0000 13.250 1.1781 0.06261 0.05395 -0.0278 0.0493 1.0000 13.500 1.1823 0.06511 0.05656 -0.0275 0.0466 1.0000 13.750 1.1872 0.06759 0.05916 -0.0273 0.0440 1.0000 14.000 1.1915 0.07013 0.06177 -0.0272 0.0419 1.0000 14.250 1.1953 0.07275 0.06441 -0.0270 0.0401 1.0000 14.500 1.2022 0.07507 0.06685 -0.0268 0.0382 1.0000 14.750 1.2088 0.07753 0.06947 -0.0267 0.0364 1.0000 15.000 1.2140 0.08016 0.07222 -0.0268 0.0347 1.0000 15.250 1.2196 0.08274 0.07487 -0.0268 0.0334 1.0000 15.500 1.2267 0.08511 0.07726 -0.0267 0.0323 1.0000 15.750 1.2327 0.08785 0.08017 -0.0268 0.0313 1.0000 16.000 1.2339 0.09137 0.08395 -0.0274 0.0301 1.0000 16.250 1.2346 0.09498 0.08777 -0.0282 0.0291 1.0000 16.500 1.2338 0.09881 0.09178 -0.0293 0.0282 1.0000 16.750 1.2325 0.10276 0.09589 -0.0306 0.0274 1.0000 17.000 1.2316 0.10670 0.09997 -0.0319 0.0268 1.0000 17.250 1.2305 0.11073 0.10414 -0.0333 0.0264 1.0000 17.500 1.2291 0.11483 0.10836 -0.0348 0.0259 1.0000 17.750 1.2245 0.11962 0.11329 -0.0368 0.0255 1.0000 18.000 1.2117 0.12619 0.12013 -0.0402 0.0254 1.0000 18.250 1.1965 0.13351 0.12772 -0.0444 0.0252 1.0000 18.500 1.1800 0.14139 0.13585 -0.0492 0.0252 1.0000 18.750 1.1608 0.15032 0.14502 -0.0549 0.0252 1.0000 19.000 1.1388 0.16057 0.15548 -0.0617 0.0252 1.0000