XFOIL Version 6.96 Calculated polar for: GOE 497 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.2576 0.09323 0.08973 -0.0595 0.9806 0.0926 -8.500 -0.4011 0.04270 0.03862 -0.1149 0.9500 0.0638 -8.250 -0.3852 0.03416 0.02916 -0.1248 0.9430 0.0648 -8.000 -0.3512 0.03036 0.02465 -0.1301 0.9404 0.0669 -7.750 -0.3341 0.02806 0.02203 -0.1301 0.9326 0.0684 -7.500 -0.3007 0.02673 0.02066 -0.1320 0.9290 0.0705 -7.250 -0.2632 0.02538 0.01911 -0.1346 0.9265 0.0729 -7.000 -0.2229 0.02410 0.01753 -0.1376 0.9248 0.0762 -6.750 -0.2018 0.02302 0.01620 -0.1369 0.9173 0.0784 -6.500 -0.1681 0.02196 0.01514 -0.1384 0.9138 0.0813 -6.250 -0.1295 0.02118 0.01425 -0.1407 0.9115 0.0854 -6.000 -0.0902 0.02021 0.01307 -0.1430 0.9095 0.0903 -5.750 -0.0502 0.01937 0.01227 -0.1454 0.9078 0.0957 -5.500 -0.0300 0.01902 0.01179 -0.1439 0.8985 0.1006 -5.250 0.0071 0.01813 0.01093 -0.1457 0.8951 0.1083 -5.000 0.0459 0.01735 0.01008 -0.1476 0.8925 0.1181 -4.750 0.0707 0.01702 0.00976 -0.1470 0.8851 0.1276 -4.500 0.1024 0.01647 0.00923 -0.1476 0.8799 0.1402 -4.250 0.1385 0.01593 0.00869 -0.1490 0.8765 0.1548 -4.000 0.1657 0.01564 0.00841 -0.1487 0.8698 0.1681 -3.750 0.1952 0.01534 0.00811 -0.1489 0.8637 0.1823 -3.500 0.2292 0.01497 0.00775 -0.1497 0.8598 0.1983 -3.250 0.2555 0.01480 0.00758 -0.1493 0.8524 0.2137 -3.000 0.2854 0.01454 0.00734 -0.1493 0.8460 0.2315 -2.750 0.3190 0.01427 0.00707 -0.1501 0.8419 0.2528 -2.500 0.3428 0.01426 0.00709 -0.1492 0.8336 0.2723 -2.250 0.3731 0.01411 0.00692 -0.1493 0.8282 0.2936 -2.000 0.4041 0.01395 0.00677 -0.1496 0.8235 0.3125 -1.750 0.4285 0.01395 0.00680 -0.1489 0.8155 0.3294 -1.500 0.4591 0.01380 0.00665 -0.1491 0.8104 0.3469 -1.250 0.4864 0.01377 0.00662 -0.1487 0.8038 0.3629 -1.000 0.5136 0.01368 0.00658 -0.1483 0.7967 0.3787 -0.750 0.5454 0.01353 0.00641 -0.1487 0.7918 0.3961 -0.500 0.5692 0.01355 0.00649 -0.1478 0.7832 0.4115 -0.250 0.5991 0.01343 0.00638 -0.1478 0.7772 0.4285 0.000 0.6257 0.01342 0.00640 -0.1474 0.7700 0.4461 0.250 0.6534 0.01335 0.00635 -0.1470 0.7625 0.4668 0.500 0.6812 0.01324 0.00630 -0.1467 0.7548 0.4874 0.750 0.7079 0.01311 0.00622 -0.1462 0.7458 0.5079 1.000 0.7349 0.01300 0.00616 -0.1457 0.7371 0.5299 1.250 0.7624 0.01284 0.00605 -0.1453 0.7280 0.5539 1.500 0.7878 0.01273 0.00605 -0.1445 0.7183 0.5811 1.750 0.8159 0.01255 0.00595 -0.1442 0.7099 0.6165 2.000 0.8388 0.01238 0.00602 -0.1430 0.6993 0.6689 2.250 0.8661 0.01171 0.00590 -0.1420 0.6897 1.0000 2.500 0.8938 0.01178 0.00583 -0.1417 0.6780 1.0000 2.750 0.9195 0.01189 0.00586 -0.1411 0.6654 1.0000 3.000 0.9459 0.01201 0.00589 -0.1406 0.6531 1.0000 3.250 0.9726 0.01214 0.00591 -0.1402 0.6408 1.0000 3.500 0.9985 0.01229 0.00598 -0.1396 0.6279 1.0000 3.750 1.0230 0.01248 0.00614 -0.1388 0.6148 1.0000 4.000 1.0482 0.01268 0.00629 -0.1381 0.6022 1.0000 4.250 1.0738 0.01290 0.00643 -0.1376 0.5904 1.0000 4.500 1.0988 0.01311 0.00660 -0.1369 0.5784 1.0000 4.750 1.1226 0.01334 0.00682 -0.1360 0.5659 1.0000 5.000 1.1469 0.01358 0.00702 -0.1352 0.5541 1.0000 5.250 1.1716 0.01383 0.00721 -0.1345 0.5429 1.0000 5.500 1.1948 0.01407 0.00745 -0.1336 0.5306 1.0000 5.750 1.2171 0.01432 0.00768 -0.1324 0.5171 1.0000 6.000 1.2386 0.01459 0.00791 -0.1311 0.5023 1.0000 6.250 1.2597 0.01489 0.00816 -0.1298 0.4877 1.0000 6.500 1.2808 0.01524 0.00845 -0.1285 0.4739 1.0000 6.750 1.3015 0.01563 0.00878 -0.1272 0.4603 1.0000 7.000 1.3221 0.01606 0.00913 -0.1259 0.4468 1.0000 7.250 1.3408 0.01646 0.00954 -0.1242 0.4324 1.0000 7.500 1.3591 0.01688 0.00996 -0.1225 0.4184 1.0000 7.750 1.3768 0.01731 0.01041 -0.1207 0.4046 1.0000 8.000 1.3935 0.01776 0.01086 -0.1188 0.3908 1.0000 8.250 1.4084 0.01821 0.01131 -0.1165 0.3766 1.0000 8.500 1.4203 0.01866 0.01175 -0.1137 0.3620 1.0000 8.750 1.4311 0.01914 0.01225 -0.1108 0.3470 1.0000 9.000 1.4414 0.01967 0.01280 -0.1079 0.3315 1.0000 9.250 1.4512 0.02028 0.01340 -0.1051 0.3156 1.0000 9.500 1.4600 0.02099 0.01410 -0.1023 0.2995 1.0000 9.750 1.4676 0.02183 0.01490 -0.0994 0.2836 1.0000 10.000 1.4740 0.02281 0.01583 -0.0966 0.2680 1.0000 10.250 1.4796 0.02392 0.01689 -0.0938 0.2526 1.0000 10.500 1.4843 0.02515 0.01808 -0.0910 0.2367 1.0000 10.750 1.4879 0.02651 0.01941 -0.0883 0.2192 1.0000 11.000 1.4902 0.02801 0.02089 -0.0857 0.1994 1.0000 11.250 1.4905 0.02973 0.02255 -0.0831 0.1784 1.0000 11.500 1.4918 0.03152 0.02426 -0.0808 0.1573 1.0000 11.750 1.4918 0.03350 0.02616 -0.0786 0.1423 1.0000 12.000 1.4913 0.03563 0.02823 -0.0766 0.1320 1.0000 12.250 1.4910 0.03785 0.03040 -0.0747 0.1239 1.0000 12.500 1.4934 0.03992 0.03251 -0.0732 0.1173 1.0000 12.750 1.4944 0.04219 0.03479 -0.0717 0.1119 1.0000 13.000 1.4951 0.04456 0.03717 -0.0703 0.1072 1.0000 13.250 1.5002 0.04659 0.03932 -0.0693 0.1026 1.0000 13.500 1.5014 0.04904 0.04178 -0.0683 0.0984 1.0000 13.750 1.5039 0.05144 0.04422 -0.0673 0.0945 1.0000 14.000 1.5084 0.05371 0.04662 -0.0667 0.0904 1.0000 14.250 1.5100 0.05632 0.04928 -0.0661 0.0865 1.0000 14.500 1.5115 0.05901 0.05201 -0.0655 0.0827 1.0000 14.750 1.5141 0.06170 0.05486 -0.0652 0.0786 1.0000 15.000 1.5135 0.06480 0.05799 -0.0651 0.0747 1.0000 15.250 1.5129 0.06798 0.06127 -0.0650 0.0705 1.0000 15.500 1.5113 0.07145 0.06486 -0.0653 0.0661 1.0000 15.750 1.5070 0.07527 0.06867 -0.0655 0.0619 1.0000 16.000 1.5037 0.07922 0.07279 -0.0662 0.0573 1.0000 16.250 1.4983 0.08332 0.07683 -0.0668 0.0536 1.0000 16.500 1.4948 0.08752 0.08124 -0.0677 0.0498 1.0000 16.750 1.4910 0.09169 0.08544 -0.0687 0.0472 1.0000