XFOIL Version 6.96 Calculated polar for: GOE 386 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.000 -0.7679 0.07530 0.07135 -0.0901 1.0000 0.0440 -16.750 -0.8075 0.06667 0.06253 -0.0956 1.0000 0.0443 -16.500 -0.8371 0.05964 0.05534 -0.1000 1.0000 0.0446 -16.250 -0.8583 0.05343 0.04897 -0.1044 0.9976 0.0448 -16.000 -0.8655 0.04756 0.04291 -0.1105 0.9886 0.0451 -15.750 -0.8650 0.04287 0.03808 -0.1157 0.9789 0.0454 -15.500 -0.8589 0.03925 0.03437 -0.1198 0.9673 0.0457 -15.250 -0.8514 0.03615 0.03119 -0.1231 0.9539 0.0459 -15.000 -0.8448 0.03360 0.02852 -0.1252 0.9400 0.0462 -14.750 -0.8389 0.03152 0.02633 -0.1262 0.9262 0.0464 -14.500 -0.8318 0.02984 0.02454 -0.1265 0.9140 0.0466 -14.250 -0.8232 0.02844 0.02304 -0.1264 0.9040 0.0469 -14.000 -0.8134 0.02726 0.02175 -0.1258 0.8940 0.0472 -13.750 -0.8022 0.02624 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0.0693 -4.250 0.0837 0.01387 0.00552 -0.1014 0.5290 0.0701 -4.000 0.1115 0.01373 0.00537 -0.1013 0.5264 0.0709 -3.750 0.1387 0.01352 0.00519 -0.1011 0.5235 0.0720 -3.500 0.1662 0.01338 0.00505 -0.1009 0.5205 0.0731 -3.250 0.1937 0.01327 0.00493 -0.1007 0.5172 0.0743 -3.000 0.2211 0.01318 0.00480 -0.1005 0.5137 0.0754 -2.750 0.2483 0.01311 0.00470 -0.1002 0.5101 0.0764 -2.500 0.2756 0.01302 0.00459 -0.1000 0.5072 0.0775 -2.250 0.3033 0.01287 0.00447 -0.0999 0.5044 0.0790 -2.000 0.3311 0.01277 0.00437 -0.0998 0.5007 0.0806 -1.750 0.3587 0.01270 0.00429 -0.0996 0.4971 0.0821 -1.500 0.3862 0.01265 0.00423 -0.0994 0.4937 0.0835 -1.250 0.4134 0.01258 0.00414 -0.0992 0.4905 0.0856 -1.000 0.4404 0.01254 0.00409 -0.0989 0.4875 0.0882 -0.750 0.4684 0.01245 0.00404 -0.0988 0.4850 0.0924 -0.500 0.4954 0.01225 0.00399 -0.0987 0.4819 0.1151 -0.250 0.5226 0.01215 0.00401 -0.0985 0.4783 0.1545 0.000 0.5498 0.01213 0.00402 -0.0983 0.4742 0.1662 0.250 0.5765 0.01214 0.00403 -0.0980 0.4699 0.1763 0.500 0.6038 0.01214 0.00406 -0.0978 0.4660 0.1853 0.750 0.6313 0.01212 0.00409 -0.0977 0.4617 0.1948 1.000 0.6584 0.01214 0.00412 -0.0975 0.4569 0.2031 1.250 0.6845 0.01216 0.00416 -0.0971 0.4518 0.2149 1.500 0.7111 0.01217 0.00421 -0.0969 0.4469 0.2277 1.750 0.7378 0.01217 0.00426 -0.0966 0.4407 0.2438 2.000 0.7630 0.01220 0.00433 -0.0961 0.4334 0.2635 2.250 0.7886 0.01221 0.00440 -0.0957 0.4256 0.2884 2.500 0.8125 0.01226 0.00450 -0.0950 0.4149 0.3188 2.750 0.8364 0.01230 0.00461 -0.0944 0.4023 0.3578 3.000 0.8585 0.01238 0.00476 -0.0934 0.3881 0.4062 3.250 0.8794 0.01246 0.00495 -0.0923 0.3738 0.4687 3.500 0.8990 0.01255 0.00518 -0.0910 0.3608 0.5459 3.750 0.9177 0.01256 0.00543 -0.0894 0.3499 0.6444 4.000 0.9347 0.01255 0.00573 -0.0874 0.3416 0.7582 4.250 0.9506 0.01258 0.00605 -0.0849 0.3345 0.8675 4.500 0.9771 0.01289 0.00643 -0.0846 0.3274 0.9637 4.750 1.0084 0.01316 0.00667 -0.0857 0.3218 1.0000 5.000 1.0272 0.01346 0.00693 -0.0842 0.3167 1.0000 5.250 1.0454 0.01382 0.00723 -0.0827 0.3121 1.0000 5.500 1.0651 0.01415 0.00753 -0.0815 0.3086 1.0000 5.750 1.0864 0.01444 0.00781 -0.0805 0.3056 1.0000 6.000 1.1070 0.01476 0.00812 -0.0795 0.3026 1.0000 6.250 1.1270 0.01513 0.00847 -0.0785 0.2997 1.0000 6.500 1.1460 0.01554 0.00886 -0.0773 0.2968 1.0000 6.750 1.1643 0.01602 0.00930 -0.0761 0.2936 1.0000 7.000 1.1839 0.01644 0.00971 -0.0752 0.2909 1.0000 7.250 1.2047 0.01681 0.01010 -0.0744 0.2883 1.0000 7.500 1.2248 0.01724 0.01053 -0.0735 0.2856 1.0000 7.750 1.2437 0.01773 0.01102 -0.0726 0.2829 1.0000 8.000 1.2619 0.01826 0.01155 -0.0716 0.2804 1.0000 8.250 1.2789 0.01887 0.01214 -0.0705 0.2779 1.0000 8.500 1.2950 0.01954 0.01280 -0.0693 0.2753 1.0000 8.750 1.3139 0.02009 0.01337 -0.0685 0.2737 1.0000 9.000 1.3330 0.02063 0.01394 -0.0678 0.2720 1.0000 9.250 1.3515 0.02121 0.01455 -0.0670 0.2700 1.0000 9.500 1.3690 0.02186 0.01522 -0.0662 0.2676 1.0000 9.750 1.3852 0.02260 0.01597 -0.0653 0.2651 1.0000 10.000 1.4005 0.02341 0.01679 -0.0644 0.2627 1.0000 10.250 1.4142 0.02434 0.01772 -0.0633 0.2604 1.0000 10.500 1.4274 0.02532 0.01871 -0.0623 0.2583 1.0000 10.750 1.4434 0.02614 0.01957 -0.0615 0.2567 1.0000 11.000 1.4600 0.02695 0.02042 -0.0609 0.2548 1.0000 11.250 1.4748 0.02788 0.02139 -0.0602 0.2525 1.0000 11.500 1.4890 0.02888 0.02243 -0.0595 0.2503 1.0000 11.750 1.5015 0.03002 0.02360 -0.0587 0.2481 1.0000 12.000 1.5127 0.03129 0.02488 -0.0579 0.2456 1.0000 12.250 1.5221 0.03275 0.02635 -0.0570 0.2432 1.0000 12.500 1.5334 0.03408 0.02771 -0.0563 0.2413 1.0000 12.750 1.5472 0.03524 0.02893 -0.0558 0.2397 1.0000 13.000 1.5598 0.03650 0.03025 -0.0553 0.2379 1.0000 13.250 1.5713 0.03787 0.03168 -0.0548 0.2358 1.0000 13.500 1.5815 0.03939 0.03324 -0.0543 0.2337 1.0000 13.750 1.5906 0.04102 0.03490 -0.0538 0.2314 1.0000 14.000 1.5977 0.04286 0.03677 -0.0533 0.2292 1.0000 14.250 1.6039 0.04477 0.03869 -0.0527 0.2269 1.0000 14.500 1.6143 0.04634 0.04033 -0.0524 0.2251 1.0000 14.750 1.6244 0.04792 0.04197 -0.0521 0.2229 1.0000 15.000 1.6317 0.04981 0.04392 -0.0517 0.2201 1.0000 15.250 1.6373 0.05186 0.04601 -0.0514 0.2170 1.0000 15.500 1.6392 0.05432 0.04848 -0.0510 0.2138 1.0000 15.750 1.6448 0.05637 0.05059 -0.0507 0.2109 1.0000 16.000 1.6507 0.05844 0.05272 -0.0504 0.2076 1.0000 16.250 1.6542 0.06077 0.05509 -0.0502 0.2039 1.0000 16.500 1.6537 0.06353 0.05788 -0.0499 0.2003 1.0000 16.750 1.6565 0.06597 0.06035 -0.0497 0.1969 1.0000 17.000 1.6596 0.06836 0.06280 -0.0496 0.1925 1.0000 17.250 1.6562 0.07152 0.06599 -0.0495 0.1880 1.0000 17.500 1.6556 0.07436 0.06886 -0.0494 0.1838 1.0000 17.750 1.6541 0.07736 0.07191 -0.0494 0.1790 1.0000 18.000 1.6488 0.08079 0.07536 -0.0494 0.1743 1.0000 18.250 1.6463 0.08394 0.07856 -0.0495 0.1700 1.0000 18.500 1.6419 0.08730 0.08195 -0.0496 0.1649 1.0000 18.750 1.6331 0.09127 0.08596 -0.0499 0.1604 1.0000 19.000 1.6290 0.09468 0.08940 -0.0502 0.1555 1.0000