XFOIL Version 6.96 Calculated polar for: GOE 390 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -0.4837 0.10952 0.10672 -0.0876 0.9139 0.0263 -17.500 -0.5182 0.10057 0.09759 -0.0924 0.8981 0.0265 -17.250 -0.5423 0.09358 0.09041 -0.0962 0.8768 0.0266 -17.000 -0.5629 0.08717 0.08382 -0.0999 0.8577 0.0267 -16.750 -0.5851 0.08060 0.07709 -0.1040 0.8431 0.0267 -16.500 -0.6161 0.07304 0.06937 -0.1090 0.8325 0.0268 -16.250 -0.6582 0.06426 0.06041 -0.1150 0.8225 0.0268 -16.000 -0.7211 0.05261 0.04855 -0.1234 0.8142 0.0268 -15.750 -0.7859 0.03909 0.03472 -0.1348 0.8055 0.0267 -15.500 -0.8045 0.03111 0.02646 -0.1442 0.7971 0.0268 -15.250 -0.8048 0.02744 0.02263 -0.1486 0.7909 0.0268 -15.000 -0.7985 0.02554 0.02061 -0.1496 0.7842 0.0269 -14.750 -0.7887 0.02429 0.01925 -0.1493 0.7776 0.0270 -14.500 -0.7780 0.02338 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0.0505 -5.000 0.1771 0.01066 0.00381 -0.1367 0.5641 0.0532 -4.750 0.2052 0.01059 0.00374 -0.1366 0.5590 0.0558 -4.500 0.2329 0.01054 0.00366 -0.1365 0.5538 0.0579 -4.250 0.2605 0.01051 0.00361 -0.1363 0.5492 0.0601 -4.000 0.2891 0.01045 0.00355 -0.1363 0.5450 0.0620 -3.750 0.3171 0.01040 0.00349 -0.1362 0.5396 0.0639 -3.500 0.3445 0.01038 0.00344 -0.1360 0.5335 0.0657 -3.250 0.3721 0.01036 0.00340 -0.1359 0.5277 0.0674 -3.000 0.3998 0.01034 0.00335 -0.1357 0.5203 0.0687 -2.750 0.4261 0.01034 0.00331 -0.1353 0.5116 0.0702 -2.500 0.4536 0.01032 0.00328 -0.1352 0.5039 0.0717 -2.250 0.4799 0.01035 0.00326 -0.1348 0.4947 0.0731 -2.000 0.5068 0.01038 0.00325 -0.1346 0.4865 0.0744 -1.750 0.5326 0.01040 0.00323 -0.1341 0.4769 0.0767 -1.500 0.5587 0.01043 0.00323 -0.1337 0.4682 0.0790 -1.250 0.5842 0.01051 0.00325 -0.1332 0.4584 0.0809 -1.000 0.6100 0.01053 0.00326 -0.1328 0.4506 0.0835 -0.750 0.6357 0.01057 0.00328 -0.1324 0.4433 0.0863 -0.500 0.6608 0.01064 0.00332 -0.1319 0.4366 0.0902 -0.250 0.6870 0.01063 0.00334 -0.1316 0.4316 0.1003 0.000 0.7123 0.01064 0.00343 -0.1311 0.4257 0.1294 0.250 0.7369 0.01074 0.00352 -0.1305 0.4196 0.1385 0.500 0.7627 0.01081 0.00358 -0.1301 0.4156 0.1445 0.750 0.7885 0.01086 0.00365 -0.1297 0.4118 0.1500 1.000 0.8128 0.01095 0.00372 -0.1291 0.4075 0.1539 1.250 0.8354 0.01106 0.00381 -0.1281 0.4030 0.1565 1.500 0.8577 0.01117 0.00391 -0.1270 0.3988 0.1603 1.750 0.8823 0.01122 0.00398 -0.1265 0.3962 0.1645 2.000 0.9067 0.01131 0.00408 -0.1259 0.3929 0.1691 2.250 0.9306 0.01143 0.00420 -0.1252 0.3892 0.1744 2.500 0.9543 0.01158 0.00435 -0.1245 0.3851 0.1820 2.750 0.9776 0.01176 0.00454 -0.1239 0.3806 0.1919 3.000 1.0032 0.01183 0.00468 -0.1236 0.3778 0.2153 3.250 1.0282 0.01190 0.00486 -0.1233 0.3745 0.2565 3.500 1.0526 0.01201 0.00505 -0.1229 0.3712 0.2932 3.750 1.0765 0.01213 0.00526 -0.1225 0.3679 0.3345 4.000 1.0997 0.01222 0.00552 -0.1220 0.3643 0.4156 4.250 1.1234 0.01227 0.00580 -0.1216 0.3612 0.5123 4.500 1.1481 0.01235 0.00603 -0.1213 0.3589 0.5697 4.750 1.1724 0.01244 0.00626 -0.1210 0.3562 0.6238 5.250 1.2143 0.01228 0.00691 -0.1189 0.3497 1.0000 5.500 1.2352 0.01262 0.00721 -0.1180 0.3459 1.0000 5.750 1.2573 0.01292 0.00750 -0.1173 0.3432 1.0000 6.000 1.2802 0.01319 0.00777 -0.1168 0.3409 1.0000 6.250 1.3022 0.01350 0.00807 -0.1162 0.3378 1.0000 6.500 1.3234 0.01386 0.00841 -0.1155 0.3341 1.0000 6.750 1.3429 0.01430 0.00882 -0.1146 0.3302 1.0000 7.000 1.3622 0.01476 0.00927 -0.1136 0.3267 1.0000 7.250 1.3842 0.01511 0.00962 -0.1131 0.3243 1.0000 7.500 1.4047 0.01553 0.01004 -0.1124 0.3209 1.0000 7.750 1.4240 0.01602 0.01052 -0.1116 0.3169 1.0000 8.000 1.4414 0.01662 0.01109 -0.1106 0.3125 1.0000 8.250 1.4596 0.01720 0.01166 -0.1098 0.3090 1.0000 8.500 1.4795 0.01769 0.01217 -0.1091 0.3058 1.0000 8.750 1.4975 0.01830 0.01278 -0.1083 0.3020 1.0000 9.000 1.5138 0.01902 0.01348 -0.1073 0.2976 1.0000 9.250 1.5287 0.01983 0.01428 -0.1063 0.2932 1.0000 9.500 1.5464 0.02050 0.01496 -0.1055 0.2894 1.0000 9.750 1.5618 0.02131 0.01576 -0.1046 0.2845 1.0000 10.000 1.5743 0.02233 0.01676 -0.1034 0.2795 1.0000 10.250 1.5897 0.02317 0.01761 -0.1025 0.2758 1.0000 10.500 1.6042 0.02408 0.01854 -0.1016 0.2718 1.0000 10.750 1.6174 0.02510 0.01955 -0.1006 0.2672 1.0000 11.000 1.6272 0.02638 0.02082 -0.0994 0.2626 1.0000 11.250 1.6417 0.02734 0.02180 -0.0986 0.2592 1.0000 11.500 1.6540 0.02847 0.02294 -0.0976 0.2549 1.0000 11.750 1.6626 0.02988 0.02435 -0.0964 0.2500 1.0000 12.000 1.6722 0.03125 0.02571 -0.0954 0.2459 1.0000 12.250 1.6835 0.03252 0.02701 -0.0945 0.2422 1.0000 12.500 1.6937 0.03387 0.02838 -0.0936 0.2384 1.0000 12.750 1.7000 0.03559 0.03010 -0.0924 0.2344 1.0000 13.000 1.7088 0.03708 0.03161 -0.0915 0.2311 1.0000 13.250 1.7184 0.03857 0.03314 -0.0907 0.2284 1.0000 13.500 1.7276 0.04009 0.03467 -0.0899 0.2252 1.0000 13.750 1.7333 0.04196 0.03656 -0.0890 0.2219 1.0000 14.000 1.7380 0.04390 0.03852 -0.0880 0.2184 1.0000 14.250 1.7447 0.04570 0.04036 -0.0872 0.2159 1.0000 14.500 1.7530 0.04736 0.04206 -0.0866 0.2132 1.0000 14.750 1.7584 0.04931 0.04404 -0.0858 0.2102 1.0000 15.000 1.7610 0.05155 0.04629 -0.0850 0.2069 1.0000 15.250 1.7613 0.05401 0.04878 -0.0840 0.2035 1.0000 15.500 1.7676 0.05592 0.05074 -0.0835 0.2014 1.0000 15.750 1.7740 0.05780 0.05265 -0.0829 0.1988 1.0000 16.000 1.7751 0.06028 0.05516 -0.0822 0.1959 1.0000 16.250 1.7750 0.06285 0.05775 -0.0815 0.1924 1.0000 16.500 1.7712 0.06587 0.06080 -0.0807 0.1891 1.0000 16.750 1.7767 0.06790 0.06288 -0.0803 0.1865 1.0000 17.000 1.7768 0.07053 0.06555 -0.0798 0.1833 1.0000 17.250 1.7756 0.07333 0.06838 -0.0793 0.1803 1.0000 17.500 1.7706 0.07657 0.07166 -0.0788 0.1774 1.0000 17.750 1.7709 0.07924 0.07438 -0.0785 0.1751 1.0000 18.000 1.7727 0.08175 0.07693 -0.0783 0.1725 1.0000 18.250 1.7699 0.08481 0.08003 -0.0780 0.1695 1.0000 18.500 1.7648 0.08814 0.08340 -0.0778 0.1665 1.0000