XFOIL Version 6.96 Calculated polar for: GOE 675 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.4556 0.03940 0.03432 -0.1412 0.9100 0.0407 -11.000 -0.4560 0.03506 0.02963 -0.1443 0.9045 0.0411 -10.750 -0.4429 0.03363 0.02811 -0.1444 0.8984 0.0415 -10.500 -0.4269 0.03222 0.02659 -0.1447 0.8934 0.0419 -10.250 -0.4094 0.03071 0.02492 -0.1449 0.8893 0.0425 -10.000 -0.3908 0.02911 0.02309 -0.1452 0.8860 0.0433 -9.750 -0.3745 0.02760 0.02136 -0.1450 0.8808 0.0440 -9.500 -0.3561 0.02610 0.01960 -0.1448 0.8761 0.0448 -9.250 -0.3351 0.02475 0.01799 -0.1446 0.8722 0.0456 -9.000 -0.3104 0.02408 0.01726 -0.1445 0.8691 0.0463 -8.750 -0.2856 0.02346 0.01656 -0.1444 0.8661 0.0471 -8.500 -0.2631 0.02284 0.01586 -0.1440 0.8614 0.0481 -8.250 -0.2393 0.02210 0.01498 -0.1437 0.8572 0.0493 -8.000 -0.2143 0.02132 0.01403 -0.1435 0.8536 0.0507 -7.750 -0.1871 0.02098 0.01366 -0.1435 0.8507 0.0521 -7.500 -0.1595 0.02054 0.01311 -0.1436 0.8482 0.0540 -7.250 -0.1359 0.02006 0.01253 -0.1431 0.8434 0.0564 -7.000 -0.1098 0.01986 0.01232 -0.1428 0.8391 0.0583 -6.750 -0.0830 0.01938 0.01169 -0.1427 0.8355 0.0616 -6.500 -0.0549 0.01914 0.01141 -0.1427 0.8326 0.0640 -6.250 -0.0263 0.01879 0.01092 -0.1428 0.8300 0.0676 -6.000 -0.0015 0.01859 0.01068 -0.1423 0.8246 0.0704 -5.750 0.0252 0.01839 0.01042 -0.1420 0.8193 0.0737 -5.500 0.0534 0.01806 0.00994 -0.1420 0.8150 0.0772 -5.250 0.0828 0.01782 0.00966 -0.1421 0.8114 0.0801 -5.000 0.1075 0.01764 0.00943 -0.1415 0.8049 0.0831 -4.750 0.1348 0.01733 0.00902 -0.1413 0.7995 0.0858 -4.500 0.1634 0.01705 0.00873 -0.1414 0.7953 0.0883 -4.250 0.1907 0.01686 0.00849 -0.1412 0.7902 0.0912 -4.000 0.2172 0.01671 0.00823 -0.1408 0.7836 0.0947 -3.750 0.2453 0.01645 0.00801 -0.1408 0.7783 0.0983 -3.500 0.2733 0.01629 0.00781 -0.1407 0.7727 0.1020 -3.250 0.2996 0.01610 0.00756 -0.1403 0.7660 0.1047 -3.000 0.3277 0.01579 0.00720 -0.1402 0.7610 0.1066 -2.750 0.3562 0.01550 0.00691 -0.1402 0.7565 0.1087 -2.500 0.3819 0.01534 0.00678 -0.1397 0.7498 0.1108 -2.250 0.4098 0.01511 0.00653 -0.1396 0.7438 0.1129 -2.000 0.4381 0.01490 0.00627 -0.1395 0.7383 0.1152 -1.750 0.4642 0.01477 0.00613 -0.1391 0.7309 0.1174 -1.500 0.4922 0.01454 0.00591 -0.1390 0.7248 0.1204 -1.250 0.5191 0.01441 0.00580 -0.1387 0.7178 0.1239 -1.000 0.5461 0.01428 0.00566 -0.1384 0.7098 0.1279 -0.750 0.5738 0.01416 0.00550 -0.1382 0.7024 0.1322 -0.500 0.5999 0.01403 0.00542 -0.1378 0.6935 0.1379 -0.250 0.6276 0.01393 0.00529 -0.1377 0.6855 0.1455 0.000 0.6535 0.01384 0.00524 -0.1372 0.6754 0.1556 0.250 0.6802 0.01375 0.00516 -0.1369 0.6655 0.1699 0.500 0.7063 0.01366 0.00513 -0.1365 0.6543 0.1914 0.750 0.7319 0.01358 0.00516 -0.1360 0.6427 0.2268 1.000 0.7577 0.01352 0.00517 -0.1356 0.6307 0.2734 1.250 0.7826 0.01348 0.00520 -0.1350 0.6170 0.3196 1.500 0.8068 0.01341 0.00527 -0.1343 0.6020 0.3792 1.750 0.8297 0.01323 0.00539 -0.1334 0.5866 0.4988 2.250 0.8791 0.01265 0.00563 -0.1315 0.5539 1.0000 2.500 0.9011 0.01291 0.00574 -0.1303 0.5365 1.0000 2.750 0.9224 0.01320 0.00589 -0.1291 0.5198 1.0000 3.000 0.9434 0.01351 0.00605 -0.1278 0.5049 1.0000 3.500 0.9853 0.01415 0.00646 -0.1252 0.4795 1.0000 3.750 1.0060 0.01449 0.00670 -0.1240 0.4690 1.0000 4.000 1.0269 0.01483 0.00695 -0.1227 0.4594 1.0000 4.250 1.0481 0.01517 0.00721 -0.1216 0.4516 1.0000 4.500 1.0692 0.01550 0.00748 -0.1204 0.4440 1.0000 5.000 1.1101 0.01619 0.00806 -0.1179 0.4307 1.0000 5.250 1.1309 0.01654 0.00838 -0.1168 0.4246 1.0000 5.500 1.1517 0.01694 0.00870 -0.1157 0.4191 1.0000 5.750 1.1732 0.01728 0.00905 -0.1147 0.4136 1.0000 6.000 1.1942 0.01764 0.00941 -0.1136 0.4080 1.0000 6.250 1.2148 0.01805 0.00977 -0.1126 0.4028 1.0000 6.500 1.2358 0.01846 0.01016 -0.1116 0.3979 1.0000 6.750 1.2560 0.01883 0.01057 -0.1105 0.3921 1.0000 7.000 1.2752 0.01927 0.01100 -0.1092 0.3861 1.0000 7.250 1.2942 0.01976 0.01144 -0.1080 0.3804 1.0000 7.500 1.3128 0.02017 0.01192 -0.1067 0.3740 1.0000 7.750 1.3305 0.02066 0.01241 -0.1053 0.3675 1.0000 8.000 1.3479 0.02120 0.01292 -0.1040 0.3617 1.0000 8.250 1.3659 0.02167 0.01347 -0.1027 0.3553 1.0000 8.500 1.3826 0.02222 0.01403 -0.1013 0.3492 1.0000 8.750 1.3991 0.02281 0.01461 -0.0999 0.3438 1.0000 9.000 1.4163 0.02336 0.01525 -0.0987 0.3375 1.0000 9.250 1.4319 0.02400 0.01591 -0.0972 0.3315 1.0000 9.500 1.4473 0.02466 0.01658 -0.0958 0.3259 1.0000 9.750 1.4631 0.02532 0.01732 -0.0945 0.3194 1.0000 10.000 1.4768 0.02609 0.01811 -0.0930 0.3130 1.0000 10.250 1.4910 0.02685 0.01892 -0.0915 0.3064 1.0000 10.500 1.5037 0.02771 0.01982 -0.0900 0.2987 1.0000 10.750 1.5147 0.02867 0.02081 -0.0883 0.2904 1.0000 11.000 1.5249 0.02972 0.02188 -0.0867 0.2809 1.0000 11.250 1.5356 0.03078 0.02298 -0.0851 0.2722 1.0000 11.500 1.5444 0.03198 0.02419 -0.0834 0.2637 1.0000 11.750 1.5545 0.03314 0.02541 -0.0819 0.2548 1.0000 12.000 1.5611 0.03457 0.02683 -0.0802 0.2458 1.0000 12.250 1.5681 0.03601 0.02830 -0.0786 0.2350 1.0000 12.500 1.5736 0.03762 0.02993 -0.0770 0.2243 1.0000 12.750 1.5777 0.03940 0.03172 -0.0754 0.2142 1.0000 13.000 1.5812 0.04131 0.03364 -0.0739 0.2036 1.0000 13.250 1.5843 0.04331 0.03567 -0.0725 0.1930 1.0000 13.500 1.5840 0.04568 0.03803 -0.0710 0.1812 1.0000 13.750 1.5816 0.04834 0.04068 -0.0696 0.1689 1.0000 14.000 1.5787 0.05117 0.04350 -0.0683 0.1575 1.0000 14.250 1.5743 0.05422 0.04656 -0.0671 0.1459 1.0000 14.500 1.5694 0.05743 0.04979 -0.0661 0.1341 1.0000 14.750 1.5628 0.06095 0.05331 -0.0653 0.1215 1.0000 15.000 1.5530 0.06495 0.05731 -0.0646 0.1077 1.0000 15.250 1.5400 0.06944 0.06179 -0.0641 0.0949 1.0000 15.500 1.5266 0.07414 0.06649 -0.0638 0.0847 1.0000 15.750 1.5138 0.07891 0.07129 -0.0638 0.0762 1.0000 16.000 1.5020 0.08367 0.07610 -0.0639 0.0686 1.0000 16.250 1.4901 0.08852 0.08101 -0.0643 0.0618 1.0000