DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il) Reynolds number: 500,000 Max Cl/Cd: 127.74 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-la203a-il-500000.txt Download as CSV file: xf-la203a-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0532 0.09706 0.09334 -0.0916 0.7620 0.0383
-9.500 -0.0459 0.09419 0.09043 -0.0932 0.7588 0.0391
-9.250 -0.0655 0.08572 0.08197 -0.1033 0.7560 0.0410
-9.000 -0.0559 0.08293 0.07921 -0.1032 0.7528 0.0412
-8.750 -0.0439 0.08089 0.07717 -0.1033 0.7493 0.0414
-8.500 -0.0321 0.07885 0.07511 -0.1038 0.7461 0.0416
-8.250 -0.0209 0.07670 0.07294 -0.1046 0.7430 0.0419
-8.000 -0.0105 0.07433 0.07057 -0.1059 0.7401 0.0423
-7.750 -0.0013 0.07163 0.06790 -0.1077 0.7368 0.0428
-7.500 -0.0368 0.05233 0.04845 -0.1381 0.7330 0.0465
-7.250 -0.0211 0.05038 0.04651 -0.1387 0.7300 0.0468
-7.000 -0.0048 0.04843 0.04452 -0.1402 0.7272 0.0470
-6.750 0.0121 0.04631 0.04237 -0.1422 0.7240 0.0473
-6.500 0.0298 0.04397 0.03998 -0.1446 0.7207 0.0478
-6.250 0.0487 0.04136 0.03726 -0.1474 0.7176 0.0487
-6.000 0.0664 0.03368 0.02887 -0.1555 0.7149 0.0528
-5.750 0.0906 0.03217 0.02732 -0.1564 0.7121 0.0532
-5.500 0.1152 0.03082 0.02595 -0.1573 0.7090 0.0538
-5.250 0.1434 0.02263 0.01675 -0.1618 0.7061 0.0456
-5.000 0.1716 0.02051 0.01440 -0.1629 0.7031 0.0446
-4.750 0.2010 0.01865 0.01224 -0.1640 0.7003 0.0441
-4.500 0.2310 0.01742 0.01076 -0.1648 0.6975 0.0442
-4.250 0.2601 0.01649 0.00969 -0.1653 0.6945 0.0445
-4.000 0.2890 0.01574 0.00883 -0.1656 0.6912 0.0450
-3.750 0.3183 0.01517 0.00814 -0.1659 0.6880 0.0456
-3.500 0.3482 0.01490 0.00774 -0.1663 0.6850 0.0463
-3.250 0.3770 0.01410 0.00694 -0.1668 0.6822 0.0474
-3.000 0.4061 0.01378 0.00662 -0.1671 0.6792 0.0483
-2.750 0.4350 0.01343 0.00629 -0.1673 0.6760 0.0493
-2.500 0.4643 0.01311 0.00597 -0.1677 0.6727 0.0503
-2.250 0.4941 0.01283 0.00566 -0.1680 0.6695 0.0514
-2.000 0.5242 0.01255 0.00534 -0.1685 0.6667 0.0525
-1.750 0.5550 0.01226 0.00506 -0.1693 0.6638 0.0543
-1.500 0.5846 0.01206 0.00492 -0.1697 0.6606 0.0564
-1.250 0.6147 0.01190 0.00476 -0.1702 0.6572 0.0584
-1.000 0.6461 0.01160 0.00449 -0.1710 0.6539 0.0609
-0.750 0.6769 0.01146 0.00435 -0.1717 0.6509 0.0638
-0.500 0.7084 0.01136 0.00421 -0.1724 0.6478 0.0676
-0.250 0.7384 0.01125 0.00416 -0.1729 0.6445 0.0731
0.000 0.7692 0.01111 0.00407 -0.1736 0.6409 0.0815
0.250 0.8013 0.01089 0.00394 -0.1745 0.6373 0.1030
0.500 0.8482 0.00967 0.00402 -0.1800 0.6340 0.5820
0.750 0.8786 0.00976 0.00415 -0.1804 0.6306 0.6339
1.000 0.9075 0.00982 0.00426 -0.1805 0.6271 0.6600
1.250 0.9363 0.00988 0.00437 -0.1805 0.6232 0.6806
1.500 0.9650 0.00995 0.00445 -0.1805 0.6194 0.6986
1.750 0.9933 0.01002 0.00454 -0.1804 0.6159 0.7125
2.000 1.0219 0.01015 0.00465 -0.1804 0.6122 0.7253
2.250 1.0501 0.01024 0.00477 -0.1804 0.6084 0.7377
2.500 1.0778 0.01027 0.00486 -0.1803 0.6044 0.7455
2.750 1.1065 0.01034 0.00491 -0.1804 0.6006 0.7518
3.000 1.1359 0.01045 0.00496 -0.1807 0.5967 0.7574
3.250 1.1636 0.01051 0.00507 -0.1807 0.5927 0.7629
3.500 1.1915 0.01058 0.00518 -0.1806 0.5884 0.7698
3.750 1.2200 0.01066 0.00527 -0.1808 0.5842 0.7768
4.000 1.2478 0.01075 0.00535 -0.1808 0.5802 0.7823
4.250 1.2757 0.01087 0.00549 -0.1808 0.5758 0.7887
4.500 1.3035 0.01095 0.00562 -0.1808 0.5710 0.7954
4.750 1.3304 0.01102 0.00573 -0.1806 0.5662 0.8016
5.000 1.3581 0.01117 0.00583 -0.1806 0.5614 0.8086
5.250 1.3847 0.01126 0.00600 -0.1804 0.5559 0.8157
5.500 1.4105 0.01133 0.00612 -0.1800 0.5494 0.8233
5.750 1.4369 0.01150 0.00623 -0.1798 0.5424 0.8320
6.000 1.4611 0.01155 0.00638 -0.1790 0.5340 0.8403
6.250 1.4857 0.01172 0.00650 -0.1784 0.5247 0.8499
6.500 1.5086 0.01181 0.00666 -0.1775 0.5141 0.8596
6.750 1.5314 0.01199 0.00685 -0.1766 0.5040 0.8707
7.000 1.5532 0.01219 0.00706 -0.1755 0.4935 0.8838
7.250 1.5740 0.01236 0.00728 -0.1741 0.4841 0.8983
7.500 1.5913 0.01259 0.00751 -0.1721 0.4745 0.9164
7.750 1.6021 0.01265 0.00767 -0.1686 0.4657 0.9511
8.000 1.6202 0.01293 0.00791 -0.1670 0.4555 0.9999
8.250 1.6436 0.01328 0.00826 -0.1665 0.4438 0.9999
8.500 1.6644 0.01370 0.00865 -0.1656 0.4319 0.9999
8.750 1.6804 0.01420 0.00911 -0.1637 0.4189 0.9999
9.000 1.6938 0.01481 0.00967 -0.1615 0.4044 0.9999
9.250 1.7062 0.01548 0.01030 -0.1592 0.3887 0.9999
9.500 1.7161 0.01630 0.01107 -0.1567 0.3719 0.9999
10.000 1.7266 0.01865 0.01329 -0.1510 0.3320 0.9999
10.250 1.7258 0.02041 0.01494 -0.1479 0.3066 0.9999
10.500 1.7206 0.02267 0.01707 -0.1447 0.2783 0.9999
10.750 1.7120 0.02538 0.01963 -0.1416 0.2506 0.9999
11.000 1.7038 0.02819 0.02231 -0.1388 0.2246 0.9999
11.250 1.6951 0.03112 0.02512 -0.1361 0.2021 0.9999
11.500 1.6877 0.03398 0.02789 -0.1336 0.1810 0.9999
11.750 1.6805 0.03688 0.03071 -0.1312 0.1626 0.9999
12.000 1.6744 0.03976 0.03352 -0.1291 0.1467 0.9999
12.250 1.6693 0.04263 0.03633 -0.1272 0.1325 0.9999
12.500 1.6652 0.04548 0.03914 -0.1254 0.1199 0.9999
12.750 1.6620 0.04834 0.04197 -0.1238 0.1085 0.9999
13.000 1.6597 0.05115 0.04475 -0.1224 0.0987 0.9999
13.250 1.6571 0.05408 0.04766 -0.1211 0.0903 0.9999
13.500 1.6543 0.05709 0.05066 -0.1198 0.0828 0.9999
13.750 1.6547 0.05980 0.05338 -0.1188 0.0766 0.9999
14.000 1.6526 0.06282 0.05641 -0.1177 0.0713 0.9999
14.250 1.6523 0.06568 0.05928 -0.1168 0.0668 0.9999
14.500 1.6508 0.06874 0.06237 -0.1160 0.0630 0.9999
14.750 1.6514 0.07158 0.06526 -0.1152 0.0597 0.9999
15.000 1.6478 0.07496 0.06864 -0.1145 0.0568 0.9999
15.250 1.6493 0.07774 0.07150 -0.1139 0.0544 0.9999
15.500 1.6491 0.08078 0.07457 -0.1134 0.0521 0.9999
15.750 1.6448 0.08436 0.07818 -0.1129 0.0501 0.9999
16.000 1.6455 0.08732 0.08121 -0.1125 0.0484 0.9999
16.250 1.6459 0.09034 0.08431 -0.1122 0.0468 0.9999
16.500 1.6445 0.09359 0.08759 -0.1119 0.0452 0.9999
16.750 1.6392 0.09740 0.09144 -0.1118 0.0439 0.9999
17.000 1.6390 0.10057 0.09467 -0.1117 0.0426 0.9999
17.250 1.6395 0.10367 0.09785 -0.1117 0.0415 0.9999
17.500 1.6398 0.10678 0.10103 -0.1117 0.0403 0.9999
17.750 1.6372 0.11032 0.10461 -0.1120 0.0392 0.9999
18.000 1.6321 0.11418 0.10850 -0.1123 0.0382 0.9999
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