XFOIL Version 6.96 Calculated polar for: GOE 420 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.7792 0.11327 0.11020 -0.0696 1.0000 0.0233 -19.500 -0.7859 0.10868 0.10554 -0.0721 1.0000 0.0233 -19.250 -0.7938 0.10387 0.10067 -0.0747 1.0000 0.0235 -19.000 -0.8013 0.09924 0.09597 -0.0772 1.0000 0.0235 -18.750 -0.8069 0.09499 0.09166 -0.0794 1.0000 0.0236 -18.500 -0.8136 0.09061 0.08722 -0.0817 1.0000 0.0237 -18.250 -0.8199 0.08641 0.08296 -0.0839 1.0000 0.0237 -18.000 -0.8259 0.08229 0.07877 -0.0860 1.0000 0.0239 -17.750 -0.8326 0.07817 0.07459 -0.0881 1.0000 0.0239 -17.500 -0.8381 0.07431 0.07067 -0.0899 1.0000 0.0240 -17.250 -0.8444 0.07041 0.06671 -0.0918 1.0000 0.0241 -17.000 -0.8526 0.06642 0.06266 -0.0936 1.0000 0.0241 -16.750 -0.8530 0.06256 0.05873 -0.0960 0.9906 0.0242 -16.500 -0.8492 0.05830 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-0.1072 0.5607 0.2620 -1.500 0.3178 0.00825 0.00210 -0.1068 0.5541 0.2773 -1.250 0.3449 0.00822 0.00210 -0.1066 0.5466 0.2903 -1.000 0.3708 0.00826 0.00210 -0.1061 0.5372 0.2992 -0.750 0.3974 0.00827 0.00210 -0.1058 0.5273 0.3064 -0.500 0.4230 0.00833 0.00212 -0.1053 0.5165 0.3125 -0.250 0.4488 0.00839 0.00214 -0.1048 0.5047 0.3172 0.000 0.4740 0.00846 0.00217 -0.1042 0.4934 0.3228 0.250 0.4986 0.00854 0.00222 -0.1035 0.4821 0.3302 0.500 0.5237 0.00862 0.00226 -0.1029 0.4714 0.3372 0.750 0.5480 0.00870 0.00232 -0.1021 0.4618 0.3452 1.000 0.5728 0.00878 0.00238 -0.1015 0.4531 0.3525 1.500 0.6224 0.00892 0.00251 -0.1002 0.4400 0.3663 1.750 0.6462 0.00902 0.00259 -0.0993 0.4326 0.3745 2.000 0.6699 0.00911 0.00267 -0.0985 0.4259 0.3841 2.250 0.6940 0.00918 0.00275 -0.0977 0.4194 0.3956 2.500 0.7165 0.00928 0.00285 -0.0967 0.4130 0.4072 2.750 0.7394 0.00936 0.00294 -0.0956 0.4080 0.4191 3.000 0.7622 0.00939 0.00301 -0.0946 0.4044 0.4314 3.250 0.7843 0.00944 0.00309 -0.0934 0.4011 0.4439 3.500 0.8057 0.00951 0.00319 -0.0921 0.3975 0.4590 3.750 0.8262 0.00961 0.00331 -0.0907 0.3936 0.4710 4.000 0.8478 0.00971 0.00343 -0.0895 0.3902 0.4824 4.250 0.8707 0.00977 0.00355 -0.0885 0.3878 0.4961 4.500 0.8931 0.00985 0.00367 -0.0875 0.3850 0.5108 4.750 0.9147 0.00994 0.00382 -0.0863 0.3820 0.5310 5.000 0.9353 0.01003 0.00399 -0.0850 0.3788 0.5565 5.250 0.9552 0.01014 0.00418 -0.0835 0.3755 0.5887 5.500 0.9749 0.01026 0.00438 -0.0820 0.3724 0.6243 5.750 0.9966 0.01034 0.00455 -0.0809 0.3701 0.6514 6.000 1.0178 0.01045 0.00472 -0.0797 0.3662 0.6731 6.250 1.0371 0.01061 0.00492 -0.0782 0.3616 0.6938 6.500 1.0537 0.01082 0.00517 -0.0763 0.3558 0.7178 6.750 1.0714 0.01086 0.00539 -0.0745 0.3509 0.7688 7.000 1.1129 0.01089 0.00580 -0.0778 0.3375 0.9689 7.250 1.1375 0.01116 0.00606 -0.0775 0.3285 1.0000 7.500 1.1541 0.01152 0.00637 -0.0758 0.3207 1.0000 7.750 1.1722 0.01184 0.00667 -0.0743 0.3118 1.0000 8.000 1.1883 0.01226 0.00704 -0.0726 0.3033 1.0000 8.250 1.2031 0.01274 0.00747 -0.0708 0.2912 1.0000 8.500 1.2172 0.01327 0.00794 -0.0689 0.2788 1.0000 8.750 1.2300 0.01388 0.00849 -0.0669 0.2665 1.0000 9.000 1.2424 0.01455 0.00909 -0.0649 0.2545 1.0000 9.250 1.2555 0.01520 0.00969 -0.0632 0.2436 1.0000 9.500 1.2693 0.01585 0.01031 -0.0615 0.2342 1.0000 9.750 1.2814 0.01661 0.01102 -0.0597 0.2248 1.0000 10.000 1.2973 0.01721 0.01161 -0.0584 0.2184 1.0000 10.250 1.3104 0.01797 0.01234 -0.0569 0.2112 1.0000 10.500 1.3250 0.01867 0.01303 -0.0556 0.2046 1.0000 10.750 1.3381 0.01948 0.01383 -0.0542 0.1974 1.0000 11.000 1.3507 0.02035 0.01467 -0.0528 0.1894 1.0000 11.250 1.3614 0.02135 0.01563 -0.0513 0.1802 1.0000 11.500 1.3669 0.02270 0.01690 -0.0494 0.1645 1.0000 11.750 1.3713 0.02419 0.01830 -0.0475 0.1480 1.0000 12.000 1.3709 0.02606 0.02008 -0.0454 0.1293 1.0000 12.250 1.3711 0.02799 0.02192 -0.0436 0.1149 1.0000 12.500 1.3749 0.02974 0.02363 -0.0421 0.1046 1.0000 12.750 1.3825 0.03126 0.02514 -0.0410 0.0983 1.0000 13.000 1.3893 0.03289 0.02677 -0.0400 0.0934 1.0000 13.250 1.3976 0.03443 0.02832 -0.0391 0.0885 1.0000 13.500 1.4054 0.03606 0.02997 -0.0382 0.0854 1.0000 13.750 1.4118 0.03783 0.03173 -0.0374 0.0811 1.0000 14.000 1.4194 0.03952 0.03345 -0.0366 0.0781 1.0000 14.250 1.4252 0.04141 0.03535 -0.0359 0.0756 1.0000 14.500 1.4326 0.04317 0.03714 -0.0353 0.0731 1.0000 14.750 1.4391 0.04506 0.03907 -0.0347 0.0711 1.0000 15.000 1.4452 0.04696 0.04099 -0.0341 0.0692 1.0000 15.250 1.4487 0.04916 0.04322 -0.0335 0.0673 1.0000 15.500 1.4546 0.05115 0.04525 -0.0331 0.0659 1.0000 15.750 1.4594 0.05327 0.04741 -0.0326 0.0643 1.0000 16.000 1.4635 0.05547 0.04965 -0.0322 0.0629 1.0000 16.250 1.4663 0.05782 0.05204 -0.0318 0.0616 1.0000 16.500 1.4679 0.06033 0.05459 -0.0314 0.0604 1.0000 16.750 1.4703 0.06276 0.05706 -0.0311 0.0590 1.0000 17.000 1.4728 0.06524 0.05960 -0.0309 0.0583 1.0000 17.250 1.4759 0.06764 0.06205 -0.0307 0.0573 1.0000 17.500 1.4757 0.07043 0.06489 -0.0306 0.0560 1.0000 17.750 1.4757 0.07323 0.06774 -0.0305 0.0550 1.0000 18.000 1.4742 0.07622 0.07077 -0.0304 0.0538 1.0000 18.250 1.4721 0.07935 0.07395 -0.0305 0.0529 1.0000 18.500 1.4740 0.08199 0.07665 -0.0306 0.0524 1.0000 18.750 1.4735 0.08494 0.07966 -0.0308 0.0517 1.0000 19.000 1.4739 0.08780 0.08258 -0.0310 0.0508 1.0000 19.250 1.4725 0.09094 0.08578 -0.0313 0.0498 1.0000