XFOIL Version 6.96 Calculated polar for: WORTMANN FX 2 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -16.000 -0.1599 0.11369 0.10745 -0.1659 0.8963 0.0340 -15.750 -0.3055 0.08209 0.07561 -0.1789 0.8959 0.0313 -15.500 -0.3450 0.07484 0.06811 -0.1810 0.8950 0.0310 -15.250 -0.3668 0.07051 0.06361 -0.1816 0.8941 0.0311 -15.000 -0.3841 0.06701 0.05994 -0.1814 0.8930 0.0313 -14.750 -0.3959 0.06429 0.05709 -0.1810 0.8919 0.0317 -14.500 -0.4065 0.06178 0.05443 -0.1802 0.8907 0.0322 -14.250 -0.4157 0.05958 0.05208 -0.1792 0.8897 0.0328 -14.000 -0.4248 0.05749 0.04981 -0.1778 0.8888 0.0336 -13.750 -0.4325 0.05559 0.04771 -0.1762 0.8880 0.0346 -13.500 -0.4380 0.05365 0.04552 -0.1745 0.8872 0.0356 -13.250 -0.4483 0.05234 0.04396 -0.1712 0.8861 0.0366 -13.000 -0.4620 0.05172 0.04321 -0.1664 0.8846 0.0373 -12.750 -0.4755 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0.7411 0.7387 2.000 0.0623 0.04477 0.03555 -0.0234 0.7393 0.7411 2.250 0.0727 0.04498 0.03576 -0.0219 0.7320 0.7432 2.500 0.0990 0.04501 0.03579 -0.0222 0.7286 0.7448 2.750 0.1294 0.04501 0.03580 -0.0232 0.7265 0.7466 3.000 0.1421 0.04526 0.03607 -0.0217 0.7196 0.7488 3.250 0.1681 0.04533 0.03614 -0.0223 0.7157 0.7509 3.500 0.2001 0.04527 0.03608 -0.0237 0.7132 0.7529 4.000 0.2444 0.04561 0.03643 -0.0243 0.7020 0.7576 4.250 0.2745 0.04551 0.03637 -0.0252 0.6993 0.7591 4.750 0.3137 0.04584 0.03680 -0.0241 0.6874 0.7624 5.000 0.3450 0.04568 0.03669 -0.0251 0.6847 0.7643 5.500 0.3864 0.04607 0.03720 -0.0247 0.6721 0.7689 5.750 0.4197 0.04586 0.03704 -0.0261 0.6695 0.7713 6.000 0.4337 0.04642 0.03765 -0.0254 0.6600 0.7735 6.250 0.4629 0.04623 0.03754 -0.0260 0.6562 0.7750 6.500 0.4955 0.04585 0.03727 -0.0269 0.6538 0.7766 6.750 0.5054 0.04651 0.03802 -0.0253 0.6430 0.7782 7.000 0.5372 0.04614 0.03775 -0.0262 0.6397 0.7799 7.500 0.5819 0.04632 0.03814 -0.0259 0.6255 0.7836 7.750 0.6167 0.04571 0.03764 -0.0270 0.6227 0.7858 8.000 0.6307 0.04624 0.03827 -0.0260 0.6108 0.7879 8.250 0.6697 0.04499 0.03713 -0.0273 0.6068 0.7901 8.500 0.6870 0.04480 0.03706 -0.0260 0.5932 0.7918 8.750 0.7075 0.04446 0.03683 -0.0249 0.5801 0.7935 9.000 0.7332 0.04392 0.03640 -0.0246 0.5690 0.7952 9.250 0.7638 0.04309 0.03570 -0.0247 0.5585 0.7969 9.500 0.7855 0.04306 0.03578 -0.0242 0.5433 0.7987 9.750 0.8117 0.04268 0.03549 -0.0241 0.5267 0.8007 10.000 0.8367 0.04244 0.03533 -0.0239 0.5064 0.8028 10.250 0.8659 0.04190 0.03481 -0.0240 0.4816 0.8050 10.500 0.8958 0.04141 0.03431 -0.0243 0.4553 0.8072 10.750 0.9209 0.04112 0.03396 -0.0238 0.4233 0.8093 11.000 0.9397 0.04137 0.03410 -0.0228 0.3848 0.8115 11.250 0.9514 0.04222 0.03474 -0.0213 0.3391 0.8137 11.500 0.9567 0.04365 0.03591 -0.0195 0.2904 0.8155 11.750 0.9583 0.04550 0.03747 -0.0176 0.2434 0.8172 12.000 0.9590 0.04757 0.03924 -0.0159 0.2004 0.8188 12.250 0.9619 0.04959 0.04104 -0.0145 0.1661 0.8204 12.500 0.9676 0.05147 0.04277 -0.0135 0.1402 0.8219 12.750 0.9756 0.05320 0.04447 -0.0127 0.1195 0.8233 13.000 0.9825 0.05500 0.04621 -0.0119 0.1035 0.8244 13.250 0.9897 0.05683 0.04803 -0.0111 0.0920 0.8256 13.500 0.9963 0.05875 0.04996 -0.0104 0.0819 0.8268 14.000 1.0088 0.06284 0.05415 -0.0091 0.0646 0.8296 14.250 1.0141 0.06505 0.05642 -0.0085 0.0572 0.8312 14.500 1.0195 0.06732 0.05876 -0.0081 0.0515 0.8330 14.750 1.0263 0.06951 0.06105 -0.0078 0.0460 0.8347 15.000 1.0308 0.07198 0.06355 -0.0076 0.0427 0.8363 15.250 1.0379 0.07423 0.06592 -0.0075 0.0398 0.8377 15.500 1.0432 0.07663 0.06842 -0.0073 0.0369 0.8390 15.750 1.0460 0.07932 0.07113 -0.0073 0.0351 0.8404 16.000 1.0531 0.08158 0.07358 -0.0072 0.0332 0.8419 16.250 1.0594 0.08397 0.07611 -0.0072 0.0318 0.8435 16.500 1.0648 0.08650 0.07875 -0.0074 0.0305 0.8452 16.750 1.0691 0.08919 0.08155 -0.0077 0.0293 0.8471 17.000 1.0731 0.09192 0.08433 -0.0081 0.0283 0.8489 17.250 1.0789 0.09457 0.08716 -0.0085 0.0272 0.8509 17.500 1.0842 0.09730 0.09009 -0.0089 0.0262 0.8528 17.750 1.0878 0.10017 0.09316 -0.0094 0.0254 0.8548 18.000 1.0906 0.10318 0.09636 -0.0100 0.0248 0.8570 18.250 1.0922 0.10638 0.09973 -0.0107 0.0242 0.8596 18.500 1.0927 0.10979 0.10330 -0.0117 0.0237 0.8625 18.750 1.0922 0.11337 0.10703 -0.0129 0.0232 0.8656 19.000 1.0910 0.11700 0.11080 -0.0142 0.0228 0.8690 19.250 1.0892 0.12068 0.11463 -0.0156 0.0223 0.8728