XFOIL Version 6.96 Calculated polar for: GOE 384 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 ------ -------- --------- --------- -------- -------- -------- -13.750 -0.5833 0.04359 0.03948 -0.1207 0.7659 0.0326 -13.500 -0.6191 0.03564 0.03107 -0.1287 0.7505 0.0327 -13.250 -0.6301 0.03256 0.02767 -0.1288 0.7308 0.0329 -13.000 -0.6338 0.03065 0.02544 -0.1272 0.7090 0.0330 -12.750 -0.6247 0.02930 0.02389 -0.1263 0.6897 0.0332 -12.500 -0.6106 0.02830 0.02273 -0.1255 0.6755 0.0334 -12.250 -0.5938 0.02747 0.02176 -0.1249 0.6647 0.0336 -12.000 -0.5753 0.02671 0.02089 -0.1243 0.6569 0.0338 -11.750 -0.5559 0.02600 0.02006 -0.1238 0.6504 0.0340 -11.500 -0.5356 0.02530 0.01925 -0.1233 0.6457 0.0342 -11.250 -0.5146 0.02458 0.01844 -0.1228 0.6418 0.0345 -11.000 -0.4930 0.02390 0.01765 -0.1224 0.6382 0.0348 -10.750 -0.4708 0.02325 0.01688 -0.1220 0.6348 0.0351 -10.500 -0.4483 0.02260 0.01610 -0.1216 0.6318 0.0355 -10.000 -0.4024 0.02123 0.01444 -0.1209 0.6269 0.0364 -9.750 -0.3787 0.02054 0.01362 -0.1205 0.6245 0.0367 -9.500 -0.3543 0.01993 0.01287 -0.1202 0.6217 0.0371 -9.250 -0.3298 0.01935 0.01220 -0.1200 0.6186 0.0374 -9.000 -0.3046 0.01890 0.01170 -0.1197 0.6156 0.0377 -8.750 -0.2788 0.01854 0.01128 -0.1195 0.6126 0.0380 -8.250 -0.2263 0.01787 0.01049 -0.1193 0.6072 0.0388 -8.000 -0.1996 0.01751 0.01009 -0.1192 0.6052 0.0392 -7.750 -0.1728 0.01716 0.00968 -0.1191 0.6031 0.0397 -7.500 -0.1459 0.01681 0.00927 -0.1190 0.6011 0.0403 -7.250 -0.1188 0.01650 0.00888 -0.1190 0.5987 0.0409 -7.000 -0.0917 0.01621 0.00849 -0.1189 0.5962 0.0415 -6.750 -0.0649 0.01589 0.00811 -0.1188 0.5936 0.0420 -6.500 -0.0380 0.01562 0.00781 -0.1187 0.5908 0.0425 -6.250 -0.0105 0.01538 0.00755 -0.1187 0.5885 0.0431 -6.000 0.0173 0.01514 0.00729 -0.1187 0.5865 0.0437 -5.750 0.0451 0.01490 0.00704 -0.1188 0.5844 0.0443 -5.500 0.0729 0.01467 0.00678 -0.1188 0.5821 0.0451 -5.250 0.1007 0.01445 0.00652 -0.1188 0.5796 0.0458 -5.000 0.1286 0.01427 0.00628 -0.1189 0.5770 0.0465 -4.750 0.1560 0.01404 0.00603 -0.1189 0.5746 0.0474 -4.500 0.1837 0.01388 0.00585 -0.1189 0.5723 0.0482 -4.250 0.2117 0.01374 0.00570 -0.1190 0.5702 0.0492 -4.000 0.2399 0.01356 0.00552 -0.1191 0.5681 0.0501 -3.750 0.2681 0.01339 0.00535 -0.1192 0.5654 0.0511 -3.500 0.2962 0.01325 0.00518 -0.1193 0.5622 0.0520 -3.250 0.3239 0.01307 0.00500 -0.1193 0.5589 0.0531 -3.000 0.3516 0.01294 0.00486 -0.1193 0.5558 0.0543 -2.750 0.3793 0.01286 0.00474 -0.1194 0.5528 0.0558 -2.500 0.4077 0.01274 0.00464 -0.1195 0.5499 0.0572 -2.250 0.4359 0.01262 0.00453 -0.1196 0.5462 0.0585 -2.000 0.4636 0.01250 0.00441 -0.1197 0.5419 0.0602 -1.750 0.4910 0.01243 0.00432 -0.1197 0.5372 0.0621 -1.500 0.5188 0.01236 0.00425 -0.1197 0.5326 0.0644 -1.250 0.5465 0.01227 0.00418 -0.1198 0.5267 0.0670 -1.000 0.5736 0.01223 0.00413 -0.1197 0.5205 0.0701 -0.750 0.6009 0.01219 0.00410 -0.1197 0.5140 0.0740 -0.500 0.6276 0.01217 0.00408 -0.1196 0.5048 0.0799 -0.250 0.6536 0.01218 0.00408 -0.1194 0.4939 0.0875 0.000 0.6784 0.01223 0.00409 -0.1190 0.4809 0.0950 0.250 0.7022 0.01234 0.00413 -0.1184 0.4674 0.1019 0.500 0.7258 0.01247 0.00419 -0.1178 0.4554 0.1093 0.750 0.7497 0.01257 0.00427 -0.1172 0.4461 0.1184 1.000 0.7728 0.01270 0.00438 -0.1166 0.4376 0.1308 1.250 0.7962 0.01261 0.00451 -0.1161 0.4310 0.2111 1.500 0.8191 0.01254 0.00467 -0.1156 0.4245 0.3092 1.750 0.8407 0.01254 0.00487 -0.1148 0.4186 0.4025 2.000 0.8640 0.01236 0.00505 -0.1144 0.4139 0.5312 2.250 0.8839 0.01204 0.00530 -0.1132 0.4095 0.7258 2.500 0.8969 0.01189 0.00560 -0.1100 0.4056 0.8860 2.750 0.9393 0.01216 0.00589 -0.1132 0.4012 0.9968 3.000 0.9609 0.01234 0.00604 -0.1123 0.3983 1.0000 3.250 0.9813 0.01254 0.00622 -0.1112 0.3952 1.0000 3.500 1.0016 0.01278 0.00642 -0.1101 0.3919 1.0000 3.750 1.0215 0.01307 0.00667 -0.1090 0.3885 1.0000 4.000 1.0410 0.01340 0.00694 -0.1079 0.3851 1.0000 4.250 1.0617 0.01371 0.00722 -0.1070 0.3823 1.0000 4.500 1.0845 0.01396 0.00746 -0.1065 0.3800 1.0000 4.750 1.1067 0.01423 0.00773 -0.1059 0.3776 1.0000 5.000 1.1284 0.01454 0.00803 -0.1053 0.3750 1.0000 5.250 1.1496 0.01488 0.00835 -0.1046 0.3724 1.0000 5.500 1.1699 0.01527 0.00871 -0.1039 0.3698 1.0000 5.750 1.1895 0.01570 0.00911 -0.1030 0.3671 1.0000 6.000 1.2096 0.01612 0.00952 -0.1023 0.3646 1.0000 6.250 1.2316 0.01646 0.00987 -0.1019 0.3625 1.0000 6.500 1.2530 0.01683 0.01025 -0.1014 0.3602 1.0000 6.750 1.2738 0.01724 0.01067 -0.1008 0.3579 1.0000 7.000 1.2937 0.01769 0.01113 -0.1002 0.3556 1.0000 7.250 1.3131 0.01818 0.01161 -0.0995 0.3534 1.0000 7.500 1.3317 0.01873 0.01215 -0.0988 0.3511 1.0000 7.750 1.3493 0.01933 0.01274 -0.0979 0.3489 1.0000 8.000 1.3684 0.01986 0.01328 -0.0973 0.3469 1.0000 8.250 1.3886 0.02034 0.01381 -0.0968 0.3450 1.0000 8.500 1.4077 0.02088 0.01438 -0.0963 0.3427 1.0000 8.750 1.4264 0.02146 0.01498 -0.0957 0.3405 1.0000 9.000 1.4441 0.02209 0.01564 -0.0950 0.3383 1.0000 9.250 1.4609 0.02279 0.01635 -0.0943 0.3362 1.0000 9.500 1.4772 0.02352 0.01708 -0.0935 0.3341 1.0000 9.750 1.4921 0.02435 0.01792 -0.0926 0.3320 1.0000 10.000 1.5084 0.02510 0.01870 -0.0919 0.3302 1.0000 10.250 1.5261 0.02578 0.01944 -0.0914 0.3280 1.0000 10.500 1.5414 0.02663 0.02033 -0.0907 0.3247 1.0000 10.750 1.5551 0.02760 0.02132 -0.0899 0.3208 1.0000 11.000 1.5664 0.02876 0.02249 -0.0889 0.3173 1.0000 11.250 1.5778 0.02993 0.02366 -0.0880 0.3141 1.0000 11.500 1.5929 0.03090 0.02469 -0.0875 0.3111 1.0000 11.750 1.6060 0.03202 0.02587 -0.0869 0.3071 1.0000 12.000 1.6163 0.03338 0.02724 -0.0861 0.3033 1.0000 12.250 1.6252 0.03485 0.02873 -0.0852 0.2999 1.0000 12.500 1.6368 0.03615 0.03006 -0.0846 0.2972 1.0000 12.750 1.6501 0.03733 0.03132 -0.0841 0.2945 1.0000 13.000 1.6609 0.03874 0.03278 -0.0835 0.2912 1.0000 13.250 1.6689 0.04040 0.03447 -0.0828 0.2874 1.0000 13.500 1.6745 0.04229 0.03636 -0.0820 0.2836 1.0000 13.750 1.6844 0.04384 0.03799 -0.0816 0.2798 1.0000 14.000 1.6919 0.04563 0.03983 -0.0810 0.2750 1.0000 14.250 1.6938 0.04796 0.04216 -0.0802 0.2697 1.0000 14.500 1.6996 0.04992 0.04417 -0.0796 0.2652 1.0000 14.750 1.7050 0.05193 0.04622 -0.0791 0.2600 1.0000 15.000 1.7047 0.05450 0.04882 -0.0783 0.2549 1.0000 15.250 1.7095 0.05658 0.05094 -0.0778 0.2503 1.0000 15.500 1.7112 0.05901 0.05341 -0.0772 0.2447 1.0000 15.750 1.7078 0.06195 0.05637 -0.0764 0.2389 1.0000 16.000 1.7080 0.06457 0.05904 -0.0759 0.2321 1.0000 16.250 1.7004 0.06804 0.06251 -0.0751 0.2248 1.0000 16.500 1.6959 0.07124 0.06575 -0.0746 0.2167 1.0000 16.750 1.6858 0.07511 0.06963 -0.0740 0.2089 1.0000 17.000 1.6751 0.07907 0.07360 -0.0734 0.1998 1.0000 17.250 1.6618 0.08343 0.07798 -0.0729 0.1913 1.0000 17.500 1.6454 0.08824 0.08282 -0.0726 0.1834 1.0000 17.750 1.6308 0.09291 0.08751 -0.0724 0.1755 1.0000