DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il) Reynolds number: 500,000 Max Cl/Cd: 124.02 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-la203a-il-500000-n5.txt Download as CSV file: xf-la203a-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0940 0.09718 0.09321 -0.0890 0.7219 0.0252
-10.000 -0.0890 0.09374 0.08976 -0.0908 0.7186 0.0253
-9.500 -0.3204 0.02818 0.02296 -0.1495 0.7147 0.0276
-9.250 -0.3025 0.02568 0.02016 -0.1515 0.7116 0.0278
-9.000 -0.2784 0.02465 0.01903 -0.1524 0.7084 0.0280
-8.750 -0.2532 0.02387 0.01817 -0.1531 0.7053 0.0282
-8.500 -0.2276 0.02314 0.01735 -0.1538 0.7024 0.0285
-8.250 -0.2016 0.02236 0.01645 -0.1545 0.6998 0.0287
-8.000 -0.1756 0.02147 0.01539 -0.1552 0.6971 0.0290
-7.750 -0.1490 0.02045 0.01423 -0.1560 0.6944 0.0293
-7.500 -0.1220 0.01949 0.01312 -0.1567 0.6915 0.0296
-7.250 -0.0946 0.01860 0.01208 -0.1574 0.6887 0.0299
-7.000 -0.0669 0.01780 0.01113 -0.1580 0.6861 0.0303
-6.750 -0.0389 0.01709 0.01027 -0.1585 0.6835 0.0307
-6.500 -0.0107 0.01647 0.00950 -0.1590 0.6810 0.0310
-6.250 0.0179 0.01589 0.00883 -0.1594 0.6784 0.0314
-6.000 0.0466 0.01540 0.00825 -0.1599 0.6755 0.0317
-5.750 0.0753 0.01485 0.00766 -0.1603 0.6728 0.0320
-5.500 0.1042 0.01447 0.00726 -0.1608 0.6700 0.0324
-5.250 0.1331 0.01416 0.00693 -0.1612 0.6672 0.0328
-5.000 0.1622 0.01389 0.00660 -0.1616 0.6646 0.0332
-4.750 0.1915 0.01360 0.00631 -0.1620 0.6619 0.0338
-4.500 0.2210 0.01333 0.00602 -0.1624 0.6592 0.0344
-4.250 0.2504 0.01306 0.00571 -0.1628 0.6562 0.0351
-4.000 0.2799 0.01280 0.00540 -0.1632 0.6532 0.0357
-3.750 0.3094 0.01255 0.00511 -0.1636 0.6503 0.0362
-3.500 0.3392 0.01226 0.00481 -0.1642 0.6477 0.0368
-3.250 0.3692 0.01205 0.00462 -0.1647 0.6449 0.0375
-3.000 0.3993 0.01186 0.00444 -0.1652 0.6417 0.0383
-2.750 0.4293 0.01168 0.00426 -0.1657 0.6384 0.0391
-2.500 0.4593 0.01152 0.00408 -0.1662 0.6352 0.0401
-2.250 0.4892 0.01140 0.00391 -0.1666 0.6322 0.0410
-2.000 0.5196 0.01124 0.00376 -0.1673 0.6292 0.0423
-1.750 0.5500 0.01111 0.00367 -0.1678 0.6260 0.0437
-1.500 0.5802 0.01100 0.00356 -0.1683 0.6226 0.0452
-1.250 0.6105 0.01091 0.00346 -0.1688 0.6190 0.0465
-1.000 0.6408 0.01080 0.00336 -0.1694 0.6156 0.0484
-0.750 0.6708 0.01075 0.00329 -0.1698 0.6126 0.0507
-0.500 0.7013 0.01067 0.00324 -0.1704 0.6092 0.0538
-0.250 0.7315 0.01060 0.00320 -0.1709 0.6054 0.0578
0.000 0.7616 0.01055 0.00318 -0.1714 0.6016 0.0632
0.250 0.7916 0.01052 0.00316 -0.1719 0.5979 0.0723
0.500 0.8217 0.01049 0.00315 -0.1724 0.5945 0.0869
0.750 0.8530 0.01036 0.00317 -0.1732 0.5908 0.1241
1.000 0.8968 0.00945 0.00326 -0.1778 0.5866 0.5038
1.250 0.9278 0.00941 0.00340 -0.1785 0.5825 0.5859
1.500 0.9571 0.00948 0.00350 -0.1787 0.5787 0.6223
1.750 0.9864 0.00954 0.00362 -0.1790 0.5751 0.6445
2.000 1.0154 0.00961 0.00372 -0.1791 0.5707 0.6623
2.250 1.0440 0.00970 0.00382 -0.1792 0.5664 0.6778
2.500 1.0723 0.00980 0.00392 -0.1793 0.5625 0.6871
2.750 1.1008 0.00990 0.00402 -0.1794 0.5588 0.6939
3.250 1.1575 0.01008 0.00423 -0.1796 0.5497 0.7040
3.500 1.1853 0.01020 0.00434 -0.1795 0.5452 0.7104
3.750 1.2133 0.01033 0.00447 -0.1796 0.5413 0.7174
4.000 1.2413 0.01042 0.00461 -0.1796 0.5369 0.7229
4.250 1.2688 0.01055 0.00475 -0.1796 0.5319 0.7285
4.500 1.2958 0.01071 0.00489 -0.1795 0.5270 0.7342
4.750 1.3233 0.01083 0.00505 -0.1795 0.5222 0.7394
5.000 1.3504 0.01096 0.00522 -0.1793 0.5165 0.7449
5.250 1.3764 0.01115 0.00540 -0.1790 0.5102 0.7515
5.500 1.4027 0.01131 0.00558 -0.1788 0.5028 0.7580
5.750 1.4273 0.01152 0.00579 -0.1783 0.4930 0.7645
6.000 1.4520 0.01174 0.00601 -0.1777 0.4814 0.7716
6.250 1.4748 0.01203 0.00627 -0.1769 0.4671 0.7784
6.500 1.4961 0.01238 0.00657 -0.1758 0.4504 0.7862
7.000 1.5351 0.01323 0.00731 -0.1731 0.4145 0.8038
7.500 1.5696 0.01421 0.00821 -0.1696 0.3809 0.8232
7.750 1.5830 0.01476 0.00873 -0.1672 0.3644 0.8342
8.000 1.5937 0.01539 0.00933 -0.1644 0.3470 0.8477
8.250 1.6026 0.01613 0.01004 -0.1614 0.3287 0.8635
8.500 1.6084 0.01702 0.01089 -0.1581 0.3088 0.8826
8.750 1.6086 0.01810 0.01194 -0.1540 0.2876 0.9112
9.000 1.6011 0.01930 0.01310 -0.1488 0.2676 0.9999
9.250 1.6021 0.02109 0.01477 -0.1461 0.2425 0.9999
9.500 1.6019 0.02312 0.01668 -0.1435 0.2195 0.9999
9.750 1.6024 0.02521 0.01868 -0.1413 0.1982 0.9999
10.000 1.6030 0.02736 0.02075 -0.1392 0.1791 0.9999
10.250 1.6040 0.02953 0.02285 -0.1372 0.1626 0.9999
10.500 1.6047 0.03174 0.02500 -0.1353 0.1477 0.9999
10.750 1.6055 0.03396 0.02718 -0.1334 0.1340 0.9999
11.000 1.6056 0.03627 0.02944 -0.1316 0.1214 0.9999
11.250 1.6051 0.03867 0.03180 -0.1298 0.1094 0.9999
11.500 1.6052 0.04107 0.03417 -0.1282 0.0990 0.9999
11.750 1.6057 0.04347 0.03654 -0.1266 0.0898 0.9999
12.000 1.6065 0.04591 0.03896 -0.1252 0.0820 0.9999
12.250 1.6087 0.04827 0.04132 -0.1240 0.0751 0.9999
12.500 1.6117 0.05058 0.04364 -0.1228 0.0696 0.9999
12.750 1.6132 0.05310 0.04616 -0.1216 0.0646 0.9999
13.000 1.6176 0.05534 0.04843 -0.1206 0.0605 0.9999
13.250 1.6196 0.05790 0.05100 -0.1197 0.0569 0.9999
13.500 1.6241 0.06019 0.05334 -0.1188 0.0539 0.9999
13.750 1.6267 0.06273 0.05591 -0.1179 0.0511 0.9999
14.000 1.6298 0.06522 0.05843 -0.1171 0.0488 0.9999
14.250 1.6329 0.06777 0.06103 -0.1164 0.0466 0.9999
14.500 1.6356 0.07036 0.06365 -0.1157 0.0445 0.9999
14.750 1.6375 0.07309 0.06643 -0.1151 0.0429 0.9999
15.000 1.6409 0.07563 0.06902 -0.1145 0.0412 0.9999
15.250 1.6425 0.07842 0.07187 -0.1140 0.0397 0.9999
15.500 1.6439 0.08126 0.07474 -0.1135 0.0383 0.9999
15.750 1.6456 0.08410 0.07764 -0.1131 0.0371 0.9999
16.000 1.6479 0.08687 0.08047 -0.1127 0.0360 0.9999
16.250 1.6492 0.08978 0.08344 -0.1124 0.0349 0.9999
16.500 1.6494 0.09282 0.08654 -0.1122 0.0338 0.9999
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