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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -1.0525 0.09130 0.08690 -0.0458 1.0000 0.1089 -19.000 -1.0493 0.08872 0.08429 -0.0465 1.0000 0.1120 -18.750 -1.0581 0.08482 0.08039 -0.0474 1.0000 0.1157 -18.500 -1.0567 0.08210 0.07767 -0.0480 1.0000 0.1194 -18.250 -1.0629 0.07856 0.07411 -0.0487 1.0000 0.1232 -18.000 -1.0637 0.07568 0.07123 -0.0493 1.0000 0.1273 -17.750 -1.0654 0.07273 0.06828 -0.0497 1.0000 0.1312 -17.500 -1.0705 0.06948 0.06503 -0.0502 1.0000 0.1357 -17.250 -1.0694 0.06691 0.06245 -0.0505 1.0000 0.1399 -17.000 -1.0772 0.06348 0.05902 -0.0508 1.0000 0.1449 -16.750 -1.0755 0.06109 0.05664 -0.0510 1.0000 0.1495 -16.500 -1.0842 0.05770 0.05325 -0.0511 1.0000 0.1547 -16.250 -1.0814 0.05552 0.05107 -0.0510 1.0000 0.1595 -16.000 -1.0912 0.05223 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0.00419 -0.0773 0.4720 0.4116 -1.750 0.1610 0.01028 0.00418 -0.0780 0.4655 0.4165 -1.500 0.1924 0.01032 0.00420 -0.0786 0.4586 0.4203 -1.250 0.2248 0.01032 0.00421 -0.0794 0.4545 0.4237 -1.000 0.2567 0.01035 0.00423 -0.0801 0.4492 0.4268 -0.750 0.2879 0.01043 0.00427 -0.0806 0.4432 0.4294 -0.500 0.3186 0.01054 0.00431 -0.0811 0.4361 0.4318 -0.250 0.3511 0.01049 0.00431 -0.0819 0.4325 0.4365 0.000 0.3829 0.01051 0.00435 -0.0826 0.4276 0.4403 0.250 0.4140 0.01058 0.00440 -0.0832 0.4219 0.4438 0.500 0.4442 0.01071 0.00448 -0.0835 0.4151 0.4468 0.750 0.4760 0.01075 0.00452 -0.0842 0.4113 0.4493 1.000 0.5074 0.01081 0.00457 -0.0847 0.4068 0.4514 1.250 0.5382 0.01086 0.00462 -0.0852 0.4014 0.4558 1.500 0.5682 0.01096 0.00471 -0.0856 0.3950 0.4599 1.750 0.5992 0.01102 0.00478 -0.0861 0.3907 0.4633 2.000 0.6303 0.01108 0.00485 -0.0866 0.3862 0.4664 2.250 0.6604 0.01119 0.00494 -0.0870 0.3808 0.4693 2.500 0.6893 0.01136 0.00505 -0.0871 0.3746 0.4718 2.750 0.7195 0.01146 0.00514 -0.0874 0.3701 0.4736 3.000 0.7501 0.01149 0.00521 -0.0879 0.3655 0.4785 3.250 0.7795 0.01160 0.00532 -0.0881 0.3601 0.4825 3.500 0.8073 0.01178 0.00547 -0.0881 0.3537 0.4860 3.750 0.8371 0.01187 0.00558 -0.0883 0.3498 0.4893 4.000 0.8661 0.01200 0.00570 -0.0885 0.3449 0.4922 4.250 0.8937 0.01217 0.00584 -0.0884 0.3394 0.4946 4.500 0.9201 0.01239 0.00602 -0.0880 0.3335 0.4964 4.750 0.9491 0.01247 0.00613 -0.0882 0.3294 0.5004 5.000 0.9764 0.01260 0.00628 -0.0881 0.3243 0.5051 5.250 1.0013 0.01282 0.00648 -0.0875 0.3185 0.5086 5.500 1.0272 0.01300 0.00666 -0.0871 0.3138 0.5118 5.750 1.0530 0.01316 0.00684 -0.0867 0.3091 0.5148 6.000 1.0760 0.01340 0.00705 -0.0858 0.3037 0.5176 6.250 1.0924 0.01369 0.00731 -0.0836 0.2982 0.5199 6.500 1.1144 0.01387 0.00750 -0.0825 0.2942 0.5216 6.750 1.1361 0.01413 0.00776 -0.0814 0.2892 0.5249 7.000 1.1562 0.01450 0.00813 -0.0802 0.2833 0.5296 7.250 1.1797 0.01478 0.00844 -0.0795 0.2789 0.5336 7.500 1.2019 0.01512 0.00879 -0.0787 0.2738 0.5372 7.750 1.2210 0.01559 0.00924 -0.0774 0.2682 0.5406 8.000 1.2418 0.01600 0.00965 -0.0765 0.2635 0.5435 8.250 1.2628 0.01641 0.01007 -0.0755 0.2585 0.5459 8.500 1.2802 0.01700 0.01062 -0.0742 0.2532 0.5478 8.750 1.2992 0.01754 0.01116 -0.0732 0.2484 0.5495 9.000 1.3195 0.01803 0.01169 -0.0724 0.2437 0.5555 9.250 1.3362 0.01873 0.01239 -0.0713 0.2383 0.5603 9.500 1.3534 0.01942 0.01311 -0.0702 0.2336 0.5642 9.750 1.3718 0.02009 0.01379 -0.0694 0.2289 0.5678 10.000 1.3859 0.02102 0.01471 -0.0682 0.2236 0.5710 10.250 1.4020 0.02187 0.01557 -0.0672 0.2192 0.5738 10.500 1.4179 0.02275 0.01645 -0.0663 0.2146 0.5762 10.750 1.4292 0.02395 0.01763 -0.0651 0.2096 0.5780 11.000 1.4446 0.02494 0.01867 -0.0644 0.2055 0.5845 11.250 1.4585 0.02608 0.01984 -0.0637 0.2012 0.5900 11.500 1.4687 0.02747 0.02125 -0.0627 0.1966 0.5944 11.750 1.4803 0.02881 0.02261 -0.0619 0.1929 0.5985 12.000 1.4931 0.03006 0.02389 -0.0612 0.1890 0.6023 12.250 1.4996 0.03185 0.02569 -0.0602 0.1850 0.6054 12.500 1.5087 0.03345 0.02730 -0.0594 0.1815 0.6078 12.750 1.5188 0.03507 0.02896 -0.0589 0.1782 0.6130 13.000 1.5269 0.03683 0.03077 -0.0583 0.1746 0.6200 13.250 1.5283 0.03925 0.03322 -0.0576 0.1709 0.6253 13.500 1.5398 0.04079 0.03481 -0.0572 0.1683 0.6305 13.750 1.5450 0.04297 0.03704 -0.0567 0.1652 0.6349 14.000 1.5481 0.04530 0.03938 -0.0562 0.1619 0.6383 14.250 1.5486 0.04796 0.04208 -0.0557 0.1590 0.6411 14.500 1.5571 0.04990 0.04409 -0.0555 0.1564 0.6496 14.750 1.5584 0.05261 0.04686 -0.0553 0.1536 0.6563 15.000 1.5584 0.05542 0.04971 -0.0550 0.1507 0.6622 15.250 1.5570 0.05841 0.05276 -0.0548 0.1483 0.6673 15.500 1.5626 0.06069 0.05508 -0.0547 0.1460 0.6715 15.750 1.5607 0.06384 0.05829 -0.0547 0.1434 0.6779 16.000 1.5579 0.06709 0.06159 -0.0547 0.1407 0.6853 16.250 1.5543 0.07048 0.06505 -0.0548 0.1383 0.6920 16.500 1.5577 0.07305 0.06769 -0.0549 0.1361 0.6987 16.750 1.5532 0.07659 0.07127 -0.0551 0.1336 0.7034 17.000 1.5483 0.08020 0.07494 -0.0554 0.1310 0.7125 17.250 1.5432 0.08388 0.07870 -0.0558 0.1288 0.7204 17.500 1.5458 0.08662 0.08150 -0.0561 0.1267 0.7282 17.750 1.5398 0.09042 0.08536 -0.0567 0.1244 0.7344 18.000 1.5352 0.09409 0.08909 -0.0573 0.1220 0.7439