XFOIL Version 6.96 Calculated polar for: GOE 449 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.000 -0.6137 0.09809 0.09559 -0.0975 0.9907 0.0228 -17.750 -0.6643 0.08564 0.08296 -0.1057 0.9883 0.0229 -17.500 -0.7182 0.07343 0.07058 -0.1144 0.9852 0.0230 -17.250 -0.7791 0.06031 0.05726 -0.1243 0.9808 0.0229 -17.000 -0.8279 0.04843 0.04515 -0.1338 0.9735 0.0229 -16.750 -0.8458 0.03984 0.03633 -0.1432 0.9677 0.0229 -16.500 -0.8426 0.03472 0.03104 -0.1500 0.9602 0.0231 -16.250 -0.8285 0.03119 0.02735 -0.1559 0.9537 0.0233 -16.000 -0.8079 0.02861 0.02463 -0.1608 0.9455 0.0234 -15.750 -0.7772 0.02649 0.02236 -0.1666 0.9399 0.0236 -15.500 -0.7479 0.02488 0.02061 -0.1709 0.9304 0.0237 -15.250 -0.7189 0.02360 0.01920 -0.1743 0.9204 0.0239 -15.000 -0.7042 0.02210 0.01755 -0.1757 0.9060 0.0242 -14.750 -0.6937 0.02115 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0.6918 0.0467 -5.000 0.0664 0.00947 0.00299 -0.1240 0.6874 0.0504 -4.750 0.0911 0.00937 0.00288 -0.1233 0.6822 0.0542 -4.500 0.1153 0.00929 0.00279 -0.1225 0.6768 0.0582 -4.250 0.1408 0.00918 0.00270 -0.1220 0.6718 0.0620 -4.000 0.1658 0.00910 0.00261 -0.1214 0.6661 0.0657 -3.750 0.1896 0.00904 0.00253 -0.1205 0.6603 0.0694 -3.500 0.2149 0.00896 0.00246 -0.1200 0.6544 0.0731 -3.250 0.2388 0.00891 0.00239 -0.1191 0.6465 0.0768 -3.000 0.2625 0.00886 0.00233 -0.1182 0.6387 0.0807 -2.750 0.2860 0.00884 0.00228 -0.1173 0.6294 0.0839 -2.500 0.3091 0.00880 0.00223 -0.1163 0.6208 0.0880 -2.250 0.3310 0.00879 0.00219 -0.1150 0.6099 0.0923 -2.000 0.3533 0.00879 0.00216 -0.1139 0.5986 0.0968 -1.750 0.3741 0.00878 0.00213 -0.1124 0.5876 0.1043 -1.500 0.3946 0.00878 0.00212 -0.1109 0.5767 0.1137 -1.250 0.4160 0.00877 0.00211 -0.1095 0.5677 0.1237 -0.750 0.4543 0.00874 0.00210 -0.1059 0.5510 0.1492 -0.500 0.4733 0.00873 0.00210 -0.1041 0.5437 0.1648 -0.250 0.4931 0.00871 0.00212 -0.1025 0.5375 0.1851 0.000 0.5142 0.00868 0.00214 -0.1011 0.5319 0.2061 0.250 0.5337 0.00868 0.00218 -0.0994 0.5261 0.2286 0.500 0.5538 0.00868 0.00223 -0.0979 0.5213 0.2540 0.750 0.5756 0.00866 0.00228 -0.0967 0.5168 0.2823 1.000 0.5964 0.00865 0.00234 -0.0953 0.5120 0.3149 1.250 0.6151 0.00863 0.00243 -0.0936 0.5071 0.3621 1.500 0.6335 0.00853 0.00254 -0.0918 0.5032 0.4431 1.750 0.6549 0.00851 0.00262 -0.0905 0.4992 0.4833 2.000 0.6743 0.00852 0.00271 -0.0889 0.4936 0.5215 2.250 0.6849 0.00833 0.00288 -0.0856 0.4874 0.6541 2.500 0.7016 0.00824 0.00299 -0.0833 0.4827 0.7255 2.750 0.7111 0.00804 0.00317 -0.0794 0.4774 0.8415 3.000 0.7340 0.00806 0.00338 -0.0783 0.4723 0.9250 3.250 0.7816 0.00823 0.00355 -0.0828 0.4678 0.9555 3.500 0.8333 0.00838 0.00370 -0.0882 0.4635 0.9676 3.750 0.8788 0.00857 0.00386 -0.0923 0.4572 0.9737 4.000 0.9148 0.00879 0.00403 -0.0944 0.4502 0.9798 4.250 0.9525 0.00894 0.00417 -0.0968 0.4452 0.9854 4.500 0.9850 0.00914 0.00434 -0.0982 0.4383 0.9921 4.750 1.0124 0.00940 0.00456 -0.0985 0.4319 1.0000 5.000 1.0277 0.00955 0.00470 -0.0962 0.4262 1.0000 5.250 1.0431 0.00975 0.00487 -0.0940 0.4200 1.0000 5.500 1.0601 0.00995 0.00505 -0.0921 0.4146 1.0000 5.750 1.0777 0.01016 0.00525 -0.0903 0.4077 1.0000 6.000 1.0935 0.01045 0.00550 -0.0884 0.3999 1.0000 6.250 1.1097 0.01076 0.00577 -0.0865 0.3887 1.0000 6.500 1.1244 0.01114 0.00609 -0.0844 0.3767 1.0000 6.750 1.1389 0.01155 0.00644 -0.0823 0.3648 1.0000 7.000 1.1546 0.01195 0.00681 -0.0805 0.3546 1.0000 7.250 1.1704 0.01238 0.00719 -0.0788 0.3439 1.0000 7.500 1.1837 0.01291 0.00767 -0.0767 0.3309 1.0000 7.750 1.1969 0.01349 0.00818 -0.0747 0.3171 1.0000 8.000 1.2118 0.01402 0.00867 -0.0731 0.3063 1.0000 8.250 1.2272 0.01456 0.00917 -0.0715 0.2968 1.0000 8.750 1.2564 0.01574 0.01029 -0.0683 0.2773 1.0000 9.000 1.2706 0.01639 0.01090 -0.0668 0.2685 1.0000 9.250 1.2860 0.01700 0.01149 -0.0654 0.2606 1.0000 9.500 1.2998 0.01770 0.01217 -0.0639 0.2523 1.0000 9.750 1.3149 0.01836 0.01282 -0.0626 0.2451 1.0000 10.000 1.3274 0.01916 0.01359 -0.0611 0.2369 1.0000 10.250 1.3412 0.01993 0.01434 -0.0597 0.2284 1.0000 10.500 1.3533 0.02081 0.01519 -0.0582 0.2213 1.0000 10.750 1.3670 0.02162 0.01600 -0.0570 0.2134 1.0000 11.000 1.3778 0.02261 0.01696 -0.0555 0.2060 1.0000 11.250 1.3906 0.02350 0.01785 -0.0542 0.1980 1.0000 11.500 1.3986 0.02472 0.01903 -0.0525 0.1872 1.0000 11.750 1.4104 0.02573 0.02003 -0.0513 0.1799 1.0000 12.000 1.4200 0.02691 0.02119 -0.0499 0.1723 1.0000 12.250 1.4262 0.02833 0.02257 -0.0483 0.1611 1.0000 12.500 1.4296 0.03000 0.02416 -0.0465 0.1473 1.0000 12.750 1.4349 0.03158 0.02571 -0.0450 0.1375 1.0000 13.000 1.4433 0.03295 0.02708 -0.0438 0.1317 1.0000 13.250 1.4459 0.03481 0.02890 -0.0422 0.1228 1.0000 13.500 1.4557 0.03613 0.03025 -0.0413 0.1193 1.0000 13.750 1.4653 0.03752 0.03167 -0.0404 0.1169 1.0000 14.000 1.4736 0.03901 0.03318 -0.0395 0.1137 1.0000 14.250 1.4782 0.04085 0.03503 -0.0383 0.1089 1.0000 14.500 1.4879 0.04227 0.03648 -0.0376 0.1068 1.0000 14.750 1.4956 0.04389 0.03815 -0.0368 0.1045 1.0000 15.000 1.5016 0.04569 0.03996 -0.0360 0.1009 1.0000 15.250 1.5071 0.04758 0.04188 -0.0352 0.0987 1.0000 15.500 1.5142 0.04932 0.04367 -0.0346 0.0958 1.0000 15.750 1.5205 0.05117 0.04555 -0.0339 0.0930 1.0000 16.000 1.5228 0.05340 0.04779 -0.0332 0.0885 1.0000 16.250 1.5269 0.05551 0.04993 -0.0326 0.0850 1.0000 16.500 1.5241 0.05834 0.05274 -0.0319 0.0769 1.0000 16.750 1.5257 0.06077 0.05519 -0.0314 0.0723 1.0000 17.000 1.5222 0.06373 0.05814 -0.0308 0.0657 1.0000 17.500 1.5185 0.06949 0.06394 -0.0300 0.0578 1.0000 17.750 1.5146 0.07263 0.06710 -0.0297 0.0537 1.0000 18.000 1.5128 0.07561 0.07012 -0.0295 0.0504 1.0000 18.250 1.5094 0.07874 0.07329 -0.0294 0.0475 1.0000 18.500 1.5057 0.08196 0.07653 -0.0293 0.0434 1.0000 18.750 1.5016 0.08529 0.07990 -0.0293 0.0409 1.0000 19.000 1.4961 0.08878 0.08340 -0.0294 0.0361 1.0000 19.250 1.4855 0.09295 0.08758 -0.0296 0.0298 1.0000