XFOIL Version 6.96 Calculated polar for: GOE 535 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -0.6843 0.10255 0.09983 -0.0646 1.0000 0.0272 -17.000 -0.7212 0.09317 0.09033 -0.0701 1.0000 0.0273 -16.750 -0.7590 0.08405 0.08108 -0.0756 1.0000 0.0273 -16.500 -0.7951 0.07562 0.07252 -0.0807 1.0000 0.0274 -16.250 -0.8295 0.06791 0.06470 -0.0852 1.0000 0.0274 -16.000 -0.8622 0.06082 0.05749 -0.0891 1.0000 0.0275 -15.750 -0.8948 0.05438 0.05095 -0.0923 1.0000 0.0275 -15.250 -0.9158 0.04250 0.03884 -0.1053 0.9961 0.0278 -15.000 -0.9193 0.03772 0.03395 -0.1112 0.9909 0.0279 -14.750 -0.9210 0.03347 0.02961 -0.1165 0.9841 0.0280 -14.500 -0.9065 0.02941 0.02545 -0.1238 0.9799 0.0282 -14.250 -0.8927 0.02628 0.02223 -0.1286 0.9728 0.0284 -14.000 -0.8655 0.02356 0.01941 -0.1345 0.9689 0.0286 -13.750 -0.8316 0.02145 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0.00967 0.00256 -0.1282 0.3806 0.1422 0.750 0.7391 0.00954 0.00257 -0.1278 0.3772 0.1932 1.250 0.7907 0.00934 0.00265 -0.1267 0.3660 0.3219 1.500 0.8171 0.00938 0.00274 -0.1262 0.3603 0.3507 1.750 0.8439 0.00944 0.00281 -0.1257 0.3554 0.3662 2.000 0.8702 0.00951 0.00291 -0.1252 0.3504 0.3814 2.250 0.8963 0.00962 0.00300 -0.1246 0.3460 0.3898 2.500 0.9228 0.00969 0.00309 -0.1241 0.3427 0.3986 2.750 0.9494 0.00977 0.00317 -0.1236 0.3391 0.4069 3.000 0.9755 0.00987 0.00326 -0.1230 0.3346 0.4125 3.250 1.0008 0.00999 0.00338 -0.1223 0.3292 0.4197 3.500 1.0264 0.01011 0.00349 -0.1216 0.3249 0.4279 3.750 1.0524 0.01020 0.00359 -0.1211 0.3213 0.4324 4.000 1.0777 0.01031 0.00370 -0.1204 0.3168 0.4380 4.250 1.1024 0.01045 0.00383 -0.1196 0.3120 0.4445 4.500 1.1271 0.01059 0.00397 -0.1188 0.3077 0.4511 4.750 1.1521 0.01070 0.00409 -0.1181 0.3036 0.4554 5.000 1.1762 0.01084 0.00423 -0.1172 0.2980 0.4608 5.250 1.1992 0.01103 0.00440 -0.1162 0.2921 0.4659 5.500 1.2232 0.01117 0.00454 -0.1153 0.2876 0.4710 5.750 1.2463 0.01133 0.00470 -0.1143 0.2822 0.4757 6.000 1.2672 0.01153 0.00488 -0.1128 0.2765 0.4811 6.250 1.2881 0.01169 0.00505 -0.1114 0.2706 0.4873 6.500 1.3076 0.01191 0.00525 -0.1097 0.2627 0.4935 6.750 1.3273 0.01215 0.00547 -0.1081 0.2562 0.4988 7.000 1.3474 0.01236 0.00569 -0.1066 0.2505 0.5054 7.250 1.3660 0.01264 0.00595 -0.1048 0.2442 0.5126 7.500 1.3855 0.01290 0.00620 -0.1032 0.2380 0.5193 7.750 1.4032 0.01321 0.00650 -0.1014 0.2304 0.5262 8.000 1.4208 0.01353 0.00681 -0.0996 0.2233 0.5333 8.250 1.4385 0.01385 0.00712 -0.0978 0.2167 0.5394 8.500 1.4553 0.01420 0.00746 -0.0959 0.2113 0.5453 8.750 1.4729 0.01452 0.00779 -0.0942 0.2056 0.5519 9.000 1.4896 0.01488 0.00815 -0.0924 0.2009 0.5581 9.250 1.5050 0.01529 0.00856 -0.0904 0.1951 0.5639 9.500 1.5218 0.01565 0.00894 -0.0887 0.1907 0.5708 9.750 1.5365 0.01611 0.00939 -0.0867 0.1862 0.5772 10.000 1.5517 0.01655 0.00985 -0.0849 0.1824 0.5841 10.250 1.5677 0.01695 0.01030 -0.0831 0.1795 0.5924 10.500 1.5819 0.01745 0.01081 -0.0813 0.1752 0.6013 10.750 1.5943 0.01803 0.01142 -0.0792 0.1710 0.6126 11.000 1.6080 0.01857 0.01201 -0.0774 0.1676 0.6267 11.250 1.6213 0.01910 0.01262 -0.0755 0.1643 0.6552 12.250 1.7456 0.02226 0.01629 -0.0842 0.1453 1.0000 12.500 1.7581 0.02318 0.01724 -0.0829 0.1423 1.0000 12.750 1.7712 0.02409 0.01818 -0.0817 0.1394 1.0000 13.000 1.7812 0.02526 0.01936 -0.0803 0.1353 1.0000 13.250 1.7891 0.02661 0.02072 -0.0789 0.1313 1.0000 13.500 1.7985 0.02789 0.02204 -0.0777 0.1272 1.0000 13.750 1.8027 0.02965 0.02379 -0.0764 0.1215 1.0000 14.000 1.8073 0.03144 0.02559 -0.0752 0.1153 1.0000 14.250 1.8057 0.03383 0.02797 -0.0738 0.1073 1.0000 14.500 1.7987 0.03685 0.03096 -0.0726 0.0972 1.0000 14.750 1.7880 0.04033 0.03443 -0.0714 0.0875 1.0000 15.000 1.7810 0.04360 0.03773 -0.0706 0.0819 1.0000 15.250 1.7707 0.04734 0.04150 -0.0699 0.0763 1.0000 15.500 1.7650 0.05066 0.04487 -0.0695 0.0729 1.0000 15.750 1.7571 0.05433 0.04859 -0.0692 0.0700 1.0000 16.000 1.7511 0.05785 0.05217 -0.0690 0.0678 1.0000 16.250 1.7458 0.06132 0.05571 -0.0689 0.0662 1.0000 16.500 1.7372 0.06527 0.05972 -0.0690 0.0644 1.0000 16.750 1.7283 0.06934 0.06386 -0.0691 0.0630 1.0000 17.000 1.7207 0.07327 0.06787 -0.0693 0.0619 1.0000 17.250 1.7135 0.07720 0.07188 -0.0696 0.0610 1.0000 17.500 1.7062 0.08118 0.07593 -0.0700 0.0602 1.0000 17.750 1.6982 0.08526 0.08009 -0.0705 0.0593 1.0000 18.000 1.6876 0.08972 0.08463 -0.0711 0.0585 1.0000 18.250 1.6773 0.09418 0.08916 -0.0717 0.0578 1.0000 18.500 1.6685 0.09846 0.09350 -0.0724 0.0570 1.0000