XFOIL Version 6.96 Calculated polar for: GOE 508 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 ------ -------- --------- --------- -------- -------- -------- -16.000 -0.7336 0.05365 0.05065 -0.1201 0.9460 0.0242 -15.750 -0.7515 0.03595 0.03244 -0.1472 0.9278 0.0243 -15.500 -0.7378 0.03076 0.02690 -0.1570 0.8890 0.0244 -15.250 -0.7463 0.02825 0.02412 -0.1573 0.8559 0.0245 -15.000 -0.7551 0.02644 0.02212 -0.1557 0.8361 0.0245 -14.750 -0.7591 0.02512 0.02066 -0.1534 0.8223 0.0245 -14.500 -0.7601 0.02410 0.01948 -0.1507 0.8100 0.0246 -14.250 -0.7600 0.02314 0.01842 -0.1478 0.7997 0.0247 -14.000 -0.7557 0.02244 0.01760 -0.1448 0.7905 0.0248 -13.750 -0.7499 0.02178 0.01684 -0.1418 0.7828 0.0249 -13.500 -0.7438 0.02122 0.01619 -0.1387 0.7760 0.0250 -13.250 -0.7344 0.02058 0.01546 -0.1362 0.7705 0.0250 -13.000 -0.7188 0.02008 0.01487 -0.1345 0.7655 0.0251 -12.750 -0.7063 0.01939 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0.2831 0.00947 0.00252 -0.1033 0.5462 0.0481 -2.250 0.3089 0.00942 0.00246 -0.1027 0.5419 0.0505 -2.000 0.3355 0.00938 0.00241 -0.1024 0.5385 0.0527 -1.750 0.3618 0.00930 0.00235 -0.1020 0.5344 0.0565 -1.500 0.3875 0.00925 0.00230 -0.1014 0.5289 0.0621 -1.000 0.4384 0.00914 0.00227 -0.1003 0.5189 0.0878 -0.750 0.4647 0.00911 0.00226 -0.0999 0.5153 0.0960 -0.500 0.4908 0.00911 0.00226 -0.0995 0.5113 0.1022 -0.250 0.5161 0.00911 0.00226 -0.0989 0.5072 0.1085 0.000 0.5421 0.00910 0.00227 -0.0985 0.5034 0.1145 0.250 0.5682 0.00908 0.00227 -0.0980 0.4996 0.1216 0.500 0.5939 0.00908 0.00228 -0.0975 0.4954 0.1298 0.750 0.6187 0.00908 0.00231 -0.0969 0.4909 0.1413 1.000 0.6432 0.00907 0.00234 -0.0962 0.4868 0.1599 1.250 0.6683 0.00901 0.00236 -0.0956 0.4823 0.1870 1.500 0.6926 0.00899 0.00240 -0.0949 0.4771 0.2168 1.750 0.7150 0.00897 0.00246 -0.0938 0.4710 0.2566 2.000 0.7381 0.00886 0.00252 -0.0929 0.4657 0.3202 2.250 0.7594 0.00872 0.00259 -0.0917 0.4599 0.4055 2.500 0.7783 0.00857 0.00268 -0.0899 0.4541 0.5073 2.750 0.7981 0.00841 0.00276 -0.0884 0.4495 0.6010 3.000 0.8155 0.00826 0.00285 -0.0862 0.4437 0.6940 3.250 0.8276 0.00813 0.00295 -0.0829 0.4377 0.7826 3.500 0.8446 0.00797 0.00311 -0.0804 0.4322 0.8937 4.000 1.0055 0.00873 0.00378 -0.1036 0.4013 0.9933 4.250 1.0568 0.00912 0.00404 -0.1090 0.3805 1.0000 4.500 1.0648 0.00944 0.00425 -0.1051 0.3605 1.0000 4.750 1.0643 0.00983 0.00451 -0.0996 0.3373 1.0000 5.000 1.0621 0.01024 0.00479 -0.0938 0.3131 1.0000 5.250 1.0647 0.01071 0.00513 -0.0890 0.2918 1.0000 5.500 1.0709 0.01119 0.00551 -0.0852 0.2730 1.0000 5.750 1.0808 0.01164 0.00588 -0.0821 0.2587 1.0000 6.000 1.0955 0.01199 0.00619 -0.0799 0.2510 1.0000 6.250 1.1096 0.01239 0.00655 -0.0777 0.2435 1.0000 6.500 1.1249 0.01278 0.00691 -0.0758 0.2371 1.0000 6.750 1.1409 0.01317 0.00728 -0.0741 0.2318 1.0000 7.000 1.1545 0.01370 0.00776 -0.0721 0.2244 1.0000 7.250 1.1722 0.01408 0.00814 -0.0707 0.2218 1.0000 7.500 1.1899 0.01448 0.00854 -0.0694 0.2187 1.0000 7.750 1.2070 0.01493 0.00899 -0.0681 0.2157 1.0000 8.000 1.2230 0.01546 0.00951 -0.0667 0.2121 1.0000 8.250 1.2383 0.01604 0.01007 -0.0653 0.2082 1.0000 8.500 1.2552 0.01657 0.01061 -0.0641 0.2058 1.0000 8.750 1.2733 0.01706 0.01112 -0.0632 0.2036 1.0000 9.000 1.2907 0.01760 0.01168 -0.0622 0.2020 1.0000 9.250 1.3071 0.01821 0.01229 -0.0611 0.1992 1.0000 9.500 1.3231 0.01887 0.01296 -0.0600 0.1970 1.0000 9.750 1.3384 0.01958 0.01367 -0.0590 0.1946 1.0000 10.000 1.3527 0.02037 0.01448 -0.0578 0.1920 1.0000 10.250 1.3687 0.02107 0.01520 -0.0569 0.1902 1.0000 10.500 1.3850 0.02177 0.01593 -0.0560 0.1887 1.0000 10.750 1.4010 0.02249 0.01668 -0.0552 0.1868 1.0000 11.000 1.4147 0.02337 0.01757 -0.0542 0.1831 1.0000 11.250 1.4264 0.02441 0.01859 -0.0530 0.1786 1.0000 11.500 1.4388 0.02542 0.01962 -0.0520 0.1749 1.0000 11.750 1.4518 0.02640 0.02060 -0.0511 0.1698 1.0000 12.000 1.4594 0.02778 0.02196 -0.0498 0.1627 1.0000 12.250 1.4705 0.02895 0.02313 -0.0488 0.1568 1.0000 12.500 1.4746 0.03066 0.02478 -0.0474 0.1460 1.0000 12.750 1.4798 0.03233 0.02643 -0.0462 0.1386 1.0000 13.000 1.4821 0.03425 0.02832 -0.0448 0.1288 1.0000 13.250 1.4854 0.03616 0.03021 -0.0436 0.1211 1.0000 13.500 1.4901 0.03800 0.03205 -0.0426 0.1161 1.0000 13.750 1.4944 0.03989 0.03393 -0.0416 0.1098 1.0000 14.000 1.4998 0.04174 0.03580 -0.0407 0.1060 1.0000 14.250 1.5042 0.04369 0.03775 -0.0399 0.1011 1.0000 14.500 1.5055 0.04596 0.04000 -0.0390 0.0938 1.0000 14.750 1.4998 0.04891 0.04290 -0.0379 0.0797 1.0000 15.000 1.4888 0.05246 0.04637 -0.0367 0.0650 1.0000 15.250 1.4889 0.05500 0.04891 -0.0361 0.0602 1.0000 15.500 1.4927 0.05721 0.05115 -0.0356 0.0581 1.0000 15.750 1.4959 0.05950 0.05347 -0.0352 0.0561 1.0000 16.000 1.4973 0.06202 0.05602 -0.0348 0.0538 1.0000 16.250 1.5017 0.06424 0.05829 -0.0345 0.0528 1.0000 16.500 1.5060 0.06651 0.06061 -0.0343 0.0515 1.0000 16.750 1.5105 0.06874 0.06288 -0.0341 0.0507 1.0000 17.000 1.5119 0.07133 0.06552 -0.0339 0.0492 1.0000 17.250 1.5151 0.07375 0.06798 -0.0338 0.0484 1.0000 17.500 1.5154 0.07655 0.07083 -0.0338 0.0473 1.0000 17.750 1.5186 0.07899 0.07331 -0.0337 0.0459 1.0000 18.000 1.5203 0.08167 0.07605 -0.0338 0.0450 1.0000 18.250 1.5222 0.08428 0.07871 -0.0339 0.0435 1.0000 18.500 1.5215 0.08726 0.08175 -0.0340 0.0424 1.0000 18.750 1.5203 0.09032 0.08484 -0.0342 0.0410 1.0000 19.000 1.5201 0.09331 0.08789 -0.0345 0.0395 1.0000 19.250 1.5170 0.09664 0.09124 -0.0349 0.0364 1.0000