DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il) Reynolds number: 200,000 Max Cl/Cd: 85.38 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-la203a-il-200000-n5.txt Download as CSV file: xf-la203a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DOUGLAS LA203A 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.0371 0.09450 0.08938 -0.0943 0.7630 0.0491
-9.000 -0.0308 0.09155 0.08640 -0.0961 0.7598 0.0504
-8.500 -0.0393 0.07948 0.07429 -0.1045 0.7534 0.0407
-8.250 -0.0291 0.07713 0.07195 -0.1053 0.7495 0.0404
-8.000 -0.0217 0.07408 0.06890 -0.1071 0.7459 0.0400
-7.750 -0.0164 0.07047 0.06527 -0.1096 0.7428 0.0395
-7.500 -0.0130 0.06617 0.06098 -0.1132 0.7394 0.0391
-7.250 -0.0138 0.06089 0.05573 -0.1185 0.7354 0.0388
-7.000 -0.0179 0.05064 0.04534 -0.1343 0.7314 0.0388
-6.750 -0.0132 0.04335 0.03770 -0.1428 0.7281 0.0390
-6.500 -0.0007 0.03762 0.03156 -0.1479 0.7248 0.0389
-6.250 0.0175 0.03298 0.02647 -0.1513 0.7212 0.0391
-6.000 0.0403 0.02941 0.02243 -0.1537 0.7181 0.0394
-5.750 0.0661 0.02668 0.01924 -0.1554 0.7153 0.0400
-5.500 0.0938 0.02447 0.01652 -0.1568 0.7127 0.0407
-5.250 0.1213 0.02337 0.01525 -0.1575 0.7096 0.0414
-5.000 0.1487 0.02275 0.01459 -0.1580 0.7061 0.0421
-4.750 0.1766 0.02207 0.01382 -0.1584 0.7030 0.0429
-4.500 0.2052 0.02124 0.01281 -0.1590 0.7003 0.0436
-4.250 0.2344 0.02040 0.01177 -0.1595 0.6978 0.0443
-4.000 0.2629 0.01966 0.01087 -0.1598 0.6948 0.0451
-3.750 0.2908 0.01902 0.01011 -0.1600 0.6911 0.0459
-3.500 0.3189 0.01847 0.00949 -0.1602 0.6878 0.0467
-3.250 0.3474 0.01806 0.00910 -0.1605 0.6848 0.0476
-3.000 0.3765 0.01775 0.00874 -0.1609 0.6821 0.0490
-2.750 0.4051 0.01742 0.00837 -0.1611 0.6790 0.0507
-2.500 0.4330 0.01709 0.00802 -0.1612 0.6752 0.0520
-2.250 0.4615 0.01673 0.00771 -0.1615 0.6718 0.0532
-2.000 0.4907 0.01645 0.00745 -0.1619 0.6685 0.0546
-1.750 0.5206 0.01619 0.00717 -0.1624 0.6657 0.0565
-1.500 0.5501 0.01600 0.00697 -0.1628 0.6625 0.0590
-1.250 0.5791 0.01581 0.00687 -0.1633 0.6587 0.0617
-1.000 0.6088 0.01565 0.00672 -0.1638 0.6550 0.0648
-0.750 0.6394 0.01546 0.00654 -0.1645 0.6517 0.0680
-0.500 0.6701 0.01534 0.00639 -0.1651 0.6489 0.0732
-0.250 0.7006 0.01523 0.00630 -0.1658 0.6458 0.0806
0.000 0.7303 0.01512 0.00626 -0.1664 0.6416 0.0911
0.250 0.7613 0.01496 0.00622 -0.1672 0.6378 0.1165
0.500 0.8038 0.01382 0.00646 -0.1716 0.6345 0.5517
0.750 0.8328 0.01386 0.00661 -0.1716 0.6315 0.6266
1.000 0.8603 0.01399 0.00680 -0.1713 0.6279 0.6648
1.250 0.8864 0.01415 0.00703 -0.1708 0.6236 0.6949
1.500 0.9133 0.01428 0.00719 -0.1703 0.6196 0.7182
1.750 0.9398 0.01437 0.00728 -0.1698 0.6161 0.7334
2.000 0.9681 0.01444 0.00730 -0.1697 0.6131 0.7429
2.250 0.9944 0.01459 0.00750 -0.1695 0.6086 0.7516
2.500 1.0216 0.01471 0.00763 -0.1693 0.6041 0.7595
2.750 1.0485 0.01479 0.00772 -0.1691 0.6002 0.7659
3.000 1.0775 0.01487 0.00775 -0.1693 0.5968 0.7720
3.250 1.1048 0.01500 0.00790 -0.1692 0.5927 0.7780
3.500 1.1302 0.01514 0.00811 -0.1688 0.5878 0.7838
3.750 1.1575 0.01526 0.00824 -0.1687 0.5835 0.7904
4.000 1.1855 0.01536 0.00832 -0.1688 0.5800 0.7966
4.250 1.2114 0.01550 0.00849 -0.1684 0.5758 0.8030
4.500 1.2370 0.01569 0.00875 -0.1681 0.5706 0.8110
4.750 1.2623 0.01583 0.00893 -0.1676 0.5660 0.8181
5.000 1.2891 0.01595 0.00904 -0.1674 0.5622 0.8259
5.250 1.3143 0.01613 0.00928 -0.1669 0.5576 0.8340
5.500 1.3373 0.01633 0.00957 -0.1661 0.5521 0.8432
5.750 1.3617 0.01647 0.00974 -0.1655 0.5471 0.8532
6.000 1.3868 0.01660 0.00986 -0.1649 0.5428 0.8641
6.250 1.4065 0.01683 0.01021 -0.1634 0.5363 0.8759
6.500 1.4274 0.01697 0.01040 -0.1621 0.5300 0.8898
6.750 1.4466 0.01709 0.01053 -0.1604 0.5236 0.9083
7.000 1.4590 0.01720 0.01075 -0.1574 0.5152 0.9421
7.250 1.4797 0.01733 0.01086 -0.1562 0.5063 0.9999
7.500 1.5012 0.01766 0.01119 -0.1554 0.4946 0.9999
7.750 1.5207 0.01804 0.01156 -0.1543 0.4820 0.9999
8.000 1.5386 0.01846 0.01194 -0.1528 0.4689 0.9999
8.250 1.5531 0.01894 0.01238 -0.1508 0.4557 0.9999
8.500 1.5664 0.01954 0.01298 -0.1487 0.4420 0.9999
8.750 1.5784 0.02023 0.01366 -0.1466 0.4281 0.9999
9.000 1.5889 0.02104 0.01444 -0.1443 0.4142 0.9999
9.250 1.5974 0.02201 0.01539 -0.1420 0.3995 0.9999
9.500 1.6042 0.02316 0.01651 -0.1396 0.3841 0.9999
9.750 1.6091 0.02452 0.01784 -0.1373 0.3675 0.9999
10.000 1.6122 0.02611 0.01938 -0.1350 0.3497 0.9999
10.250 1.6134 0.02794 0.02117 -0.1327 0.3306 0.9999
10.500 1.6119 0.03008 0.02324 -0.1304 0.3095 0.9999
10.750 1.6073 0.03255 0.02563 -0.1280 0.2876 0.9999
11.000 1.6006 0.03527 0.02827 -0.1257 0.2652 0.9999
11.250 1.5926 0.03819 0.03110 -0.1234 0.2434 0.9999
11.500 1.5840 0.04125 0.03407 -0.1213 0.2234 0.9999
11.750 1.5758 0.04439 0.03713 -0.1193 0.2051 0.9999
12.000 1.5691 0.04751 0.04019 -0.1176 0.1879 0.9999
12.250 1.5633 0.05063 0.04326 -0.1160 0.1722 0.9999
12.500 1.5582 0.05378 0.04636 -0.1147 0.1574 0.9999
13.000 1.5508 0.06004 0.05257 -0.1124 0.1321 0.9999
13.250 1.5483 0.06313 0.05564 -0.1114 0.1211 0.9999
13.500 1.5459 0.06627 0.05878 -0.1106 0.1117 0.9999
13.750 1.5431 0.06950 0.06200 -0.1098 0.1034 0.9999
14.000 1.5422 0.07255 0.06507 -0.1091 0.0956 0.9999
14.250 1.5409 0.07570 0.06823 -0.1086 0.0891 0.9999
14.500 1.5390 0.07895 0.07150 -0.1080 0.0832 0.9999
14.750 1.5389 0.08203 0.07462 -0.1076 0.0779 0.9999
15.000 1.5371 0.08535 0.07795 -0.1073 0.0734 0.9999
15.250 1.5373 0.08842 0.08108 -0.1070 0.0693 0.9999
15.500 1.5363 0.09169 0.08438 -0.1068 0.0657 0.9999
15.750 1.5357 0.09493 0.08768 -0.1067 0.0626 0.9999
16.000 1.5361 0.09807 0.09088 -0.1067 0.0597 0.9999
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