XFOIL Version 6.96 Calculated polar for: AH 93-W-300 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -1.0162 0.09216 0.08705 -0.0468 1.0000 0.1345 -18.750 -1.0170 0.08904 0.08388 -0.0477 1.0000 0.1390 -18.500 -1.0214 0.08565 0.08055 -0.0485 1.0000 0.1437 -18.250 -1.0236 0.08245 0.07731 -0.0493 1.0000 0.1486 -18.000 -1.0274 0.07922 0.07412 -0.0500 1.0000 0.1534 -17.750 -1.0297 0.07608 0.07095 -0.0506 1.0000 0.1586 -17.500 -1.0332 0.07295 0.06786 -0.0512 1.0000 0.1636 -17.250 -1.0350 0.06999 0.06488 -0.0517 1.0000 0.1690 -17.000 -1.0383 0.06696 0.06187 -0.0521 1.0000 0.1741 -16.750 -1.0397 0.06413 0.05903 -0.0524 1.0000 0.1797 -16.500 -1.0425 0.06125 0.05617 -0.0527 1.0000 0.1848 -16.250 -1.0439 0.05856 0.05348 -0.0529 1.0000 0.1904 -16.000 -1.0454 0.05590 0.05081 -0.0530 1.0000 0.1956 -15.750 -1.0470 0.05334 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-0.0755 0.4925 0.4493 -1.000 0.2396 0.01329 0.00623 -0.0760 0.4861 0.4517 -0.750 0.2700 0.01324 0.00623 -0.0765 0.4805 0.4561 -0.500 0.3010 0.01325 0.00629 -0.0770 0.4750 0.4596 -0.250 0.3317 0.01332 0.00635 -0.0775 0.4691 0.4628 0.000 0.3617 0.01343 0.00641 -0.0778 0.4631 0.4661 0.250 0.3922 0.01355 0.00649 -0.0783 0.4574 0.4694 0.500 0.4234 0.01360 0.00654 -0.0788 0.4524 0.4723 0.750 0.4537 0.01363 0.00655 -0.0793 0.4468 0.4755 1.000 0.4829 0.01368 0.00660 -0.0795 0.4410 0.4793 1.250 0.5124 0.01382 0.00673 -0.0797 0.4352 0.4825 1.500 0.5428 0.01387 0.00683 -0.0801 0.4306 0.4858 1.750 0.5726 0.01396 0.00692 -0.0804 0.4252 0.4892 2.000 0.6016 0.01410 0.00701 -0.0806 0.4197 0.4925 2.250 0.6302 0.01431 0.00715 -0.0807 0.4137 0.4952 2.500 0.6602 0.01436 0.00723 -0.0811 0.4094 0.4976 2.750 0.6890 0.01435 0.00727 -0.0812 0.4041 0.5023 3.000 0.7168 0.01447 0.00739 -0.0812 0.3987 0.5058 3.250 0.7435 0.01471 0.00759 -0.0810 0.3927 0.5090 3.500 0.7723 0.01478 0.00771 -0.0811 0.3884 0.5123 3.750 0.8003 0.01490 0.00784 -0.0810 0.3832 0.5156 4.000 0.8267 0.01509 0.00799 -0.0808 0.3778 0.5187 4.250 0.8518 0.01537 0.00820 -0.0803 0.3721 0.5212 4.500 0.8793 0.01540 0.00829 -0.0802 0.3677 0.5249 4.750 0.9051 0.01550 0.00843 -0.0798 0.3625 0.5290 5.000 0.9287 0.01570 0.00863 -0.0791 0.3573 0.5324 5.250 0.9507 0.01598 0.00889 -0.0781 0.3520 0.5357 5.500 0.9742 0.01612 0.00909 -0.0772 0.3476 0.5392 5.750 0.9931 0.01632 0.00930 -0.0756 0.3426 0.5425 6.000 1.0103 0.01662 0.00957 -0.0738 0.3375 0.5454 6.250 1.0300 0.01698 0.00990 -0.0725 0.3326 0.5478 6.500 1.0537 0.01722 0.01018 -0.0719 0.3278 0.5508 6.750 1.0750 0.01752 0.01051 -0.0710 0.3226 0.5558 7.000 1.0933 0.01800 0.01097 -0.0696 0.3173 0.5596 7.250 1.1149 0.01837 0.01140 -0.0688 0.3127 0.5632 7.500 1.1359 0.01877 0.01183 -0.0680 0.3075 0.5667 7.750 1.1536 0.01933 0.01237 -0.0668 0.3023 0.5700 8.000 1.1709 0.01994 0.01297 -0.0656 0.2973 0.5732 8.250 1.1915 0.02043 0.01350 -0.0649 0.2924 0.5761 8.500 1.2090 0.02108 0.01413 -0.0638 0.2871 0.5786 8.750 1.2226 0.02190 0.01494 -0.0625 0.2818 0.5841 9.000 1.2433 0.02243 0.01556 -0.0620 0.2771 0.5885 9.250 1.2594 0.02323 0.01639 -0.0611 0.2719 0.5923 9.500 1.2717 0.02427 0.01741 -0.0598 0.2667 0.5959 9.750 1.2886 0.02510 0.01829 -0.0591 0.2621 0.5997 10.000 1.3039 0.02606 0.01927 -0.0583 0.2570 0.6035 10.250 1.3142 0.02735 0.02053 -0.0573 0.2520 0.6065 10.500 1.3286 0.02844 0.02164 -0.0565 0.2475 0.6093 10.750 1.3431 0.02952 0.02279 -0.0560 0.2426 0.6154 11.000 1.3520 0.03102 0.02430 -0.0551 0.2377 0.6200 11.250 1.3633 0.03239 0.02572 -0.0544 0.2334 0.6244 11.500 1.3751 0.03378 0.02717 -0.0538 0.2287 0.6288 11.750 1.3826 0.03550 0.02888 -0.0531 0.2241 0.6330 12.000 1.3894 0.03733 0.03072 -0.0524 0.2199 0.6370 12.250 1.4007 0.03886 0.03229 -0.0520 0.2156 0.6403 12.500 1.4063 0.04091 0.03438 -0.0515 0.2113 0.6465 12.750 1.4105 0.04307 0.03657 -0.0509 0.2072 0.6519 13.000 1.4197 0.04491 0.03850 -0.0507 0.2034 0.6572 13.250 1.4256 0.04702 0.04065 -0.0504 0.1994 0.6624 13.500 1.4250 0.04978 0.04340 -0.0499 0.1956 0.6670 13.750 1.4333 0.05177 0.04544 -0.0498 0.1922 0.6714 14.000 1.4377 0.05419 0.04793 -0.0497 0.1885 0.6780 14.250 1.4392 0.05684 0.05063 -0.0496 0.1849 0.6843 14.500 1.4396 0.05968 0.05351 -0.0495 0.1816 0.6904 14.750 1.4459 0.06197 0.05588 -0.0495 0.1784 0.6967 15.000 1.4472 0.06483 0.05877 -0.0496 0.1750 0.7018 15.250 1.4454 0.06795 0.06191 -0.0497 0.1718 0.7082 15.500 1.4487 0.07060 0.06466 -0.0498 0.1689 0.7159 15.750 1.4511 0.07340 0.06755 -0.0501 0.1659 0.7235 16.000 1.4514 0.07642 0.07059 -0.0503 0.1628 0.7306 16.250 1.4475 0.07990 0.07408 -0.0507 0.1598 0.7377 16.500 1.4519 0.08252 0.07684 -0.0510 0.1571 0.7466 16.750 1.4516 0.08570 0.08009 -0.0515 0.1542 0.7551 17.000 1.4503 0.08898 0.08339 -0.0520 0.1514 0.7631 17.250 1.4493 0.09216 0.08662 -0.0525 0.1487 0.7729 17.500 1.4504 0.09527 0.08985 -0.0531 0.1461 0.7835 17.750 1.4515 0.09828 0.09295 -0.0537 0.1434 0.7947 18.000 1.4485 0.10177 0.09648 -0.0544 0.1409 0.8072 18.250 1.4485 0.10483 0.09959 -0.0550 0.1384 0.8204 18.500 1.4502 0.10781 0.10269 -0.0557 0.1359 0.8359 18.750 1.4474 0.11124 0.10622 -0.0565 0.1333 0.8522 19.000 1.4463 0.11431 0.10933 -0.0571 0.1309 0.8711 19.250 1.4457 0.11715 0.11226 -0.0574 0.1286 0.8948