DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il) Reynolds number: 1,000,000 Max Cl/Cd: 151.54 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-la203a-il-1000000-n5.txt Download as CSV file: xf-la203a-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6454 0.03747 0.03365 -0.1340 0.7403 0.0233
-13.000 -0.6571 0.03190 0.02785 -0.1403 0.7348 0.0234
-12.500 -0.6421 0.02636 0.02192 -0.1472 0.7223 0.0235
-12.250 -0.6236 0.02466 0.02005 -0.1494 0.7172 0.0236
-11.750 -0.5810 0.02224 0.01731 -0.1517 0.7096 0.0238
-11.500 -0.5576 0.02128 0.01623 -0.1525 0.7064 0.0239
-11.250 -0.5336 0.02036 0.01519 -0.1533 0.7032 0.0239
-11.000 -0.5100 0.01924 0.01393 -0.1541 0.7002 0.0242
-10.750 -0.4847 0.01848 0.01307 -0.1548 0.6974 0.0243
-10.500 -0.4582 0.01784 0.01237 -0.1554 0.6953 0.0245
-10.250 -0.4311 0.01729 0.01177 -0.1559 0.6931 0.0247
-10.000 -0.4037 0.01681 0.01124 -0.1564 0.6906 0.0248
-9.750 -0.3760 0.01641 0.01079 -0.1569 0.6879 0.0250
-9.500 -0.3482 0.01603 0.01036 -0.1573 0.6855 0.0252
-9.250 -0.3203 0.01566 0.00993 -0.1577 0.6832 0.0254
-9.000 -0.2924 0.01529 0.00949 -0.1581 0.6807 0.0256
-8.750 -0.2639 0.01485 0.00902 -0.1586 0.6787 0.0258
-8.500 -0.2352 0.01443 0.00855 -0.1591 0.6764 0.0260
-8.250 -0.2065 0.01404 0.00810 -0.1596 0.6739 0.0262
-8.000 -0.1777 0.01366 0.00767 -0.1600 0.6715 0.0264
-7.750 -0.1489 0.01330 0.00726 -0.1605 0.6689 0.0267
-7.500 -0.1200 0.01298 0.00687 -0.1609 0.6662 0.0269
-7.250 -0.0910 0.01267 0.00651 -0.1613 0.6637 0.0271
-7.000 -0.0616 0.01236 0.00617 -0.1618 0.6614 0.0273
-6.750 -0.0321 0.01208 0.00585 -0.1622 0.6589 0.0275
-6.500 -0.0025 0.01183 0.00556 -0.1627 0.6563 0.0276
-6.250 0.0271 0.01147 0.00517 -0.1632 0.6534 0.0280
-6.000 0.0566 0.01121 0.00488 -0.1637 0.6504 0.0283
-5.500 0.1162 0.01081 0.00445 -0.1646 0.6454 0.0290
-5.250 0.1462 0.01062 0.00426 -0.1651 0.6428 0.0293
-5.000 0.1762 0.01045 0.00407 -0.1656 0.6399 0.0297
-4.750 0.2061 0.01028 0.00388 -0.1660 0.6367 0.0301
-4.500 0.2360 0.01013 0.00370 -0.1665 0.6336 0.0306
-4.250 0.2658 0.01000 0.00354 -0.1669 0.6306 0.0310
-4.000 0.2961 0.00987 0.00340 -0.1674 0.6281 0.0315
-3.750 0.3265 0.00972 0.00324 -0.1679 0.6252 0.0319
-3.500 0.3570 0.00955 0.00307 -0.1685 0.6219 0.0326
-3.250 0.3873 0.00943 0.00295 -0.1690 0.6185 0.0332
-3.000 0.4172 0.00934 0.00285 -0.1695 0.6150 0.0338
-2.750 0.4474 0.00925 0.00275 -0.1699 0.6120 0.0345
-2.500 0.4779 0.00916 0.00265 -0.1704 0.6092 0.0352
-2.250 0.5082 0.00907 0.00257 -0.1709 0.6057 0.0359
-2.000 0.5386 0.00899 0.00247 -0.1714 0.6021 0.0367
-1.750 0.5688 0.00892 0.00240 -0.1719 0.5985 0.0377
-1.500 0.5987 0.00888 0.00236 -0.1723 0.5950 0.0390
-1.250 0.6291 0.00882 0.00231 -0.1728 0.5919 0.0403
-1.000 0.6594 0.00877 0.00226 -0.1733 0.5882 0.0416
-0.750 0.6896 0.00872 0.00223 -0.1738 0.5843 0.0434
-0.500 0.7194 0.00871 0.00221 -0.1742 0.5802 0.0453
-0.250 0.7494 0.00869 0.00219 -0.1746 0.5767 0.0476
0.000 0.7797 0.00866 0.00218 -0.1751 0.5732 0.0511
0.250 0.8098 0.00863 0.00218 -0.1755 0.5691 0.0562
0.500 0.8397 0.00863 0.00219 -0.1760 0.5648 0.0643
0.750 0.8694 0.00863 0.00222 -0.1764 0.5606 0.0784
1.000 0.8997 0.00860 0.00224 -0.1769 0.5571 0.0912
1.250 0.9312 0.00851 0.00227 -0.1777 0.5529 0.1425
1.500 0.9744 0.00773 0.00237 -0.1820 0.5487 0.5068
1.750 1.0053 0.00772 0.00248 -0.1827 0.5445 0.5734
2.000 1.0351 0.00776 0.00257 -0.1831 0.5407 0.6021
2.250 1.0646 0.00781 0.00266 -0.1834 0.5363 0.6212
2.500 1.0937 0.00789 0.00275 -0.1837 0.5316 0.6395
2.750 1.1224 0.00798 0.00286 -0.1838 0.5272 0.6529
3.250 1.1800 0.00814 0.00304 -0.1842 0.5192 0.6643
3.500 1.2084 0.00825 0.00314 -0.1843 0.5140 0.6694
3.750 1.2361 0.00839 0.00326 -0.1843 0.5087 0.6745
4.000 1.2646 0.00848 0.00336 -0.1844 0.5043 0.6788
4.250 1.2926 0.00859 0.00348 -0.1845 0.4983 0.6840
4.500 1.3195 0.00876 0.00364 -0.1843 0.4910 0.6908
4.750 1.3472 0.00889 0.00377 -0.1843 0.4825 0.6972
5.000 1.3732 0.00911 0.00394 -0.1841 0.4714 0.7021
5.250 1.3987 0.00936 0.00415 -0.1837 0.4573 0.7075
5.500 1.4232 0.00966 0.00438 -0.1832 0.4403 0.7129
5.750 1.4465 0.01003 0.00465 -0.1824 0.4206 0.7179
6.000 1.4688 0.01045 0.00498 -0.1816 0.3976 0.7235
6.250 1.4896 0.01094 0.00536 -0.1805 0.3736 0.7301
6.500 1.5100 0.01144 0.00575 -0.1793 0.3524 0.7365
6.750 1.5304 0.01191 0.00614 -0.1781 0.3328 0.7427
7.000 1.5492 0.01245 0.00659 -0.1767 0.3113 0.7496
7.250 1.5652 0.01309 0.00712 -0.1748 0.2875 0.7565
7.500 1.5782 0.01382 0.00773 -0.1724 0.2617 0.7642
7.750 1.5839 0.01468 0.00847 -0.1687 0.2362 0.7735
8.000 1.5913 0.01557 0.00927 -0.1655 0.2126 0.7825
8.250 1.5961 0.01663 0.01023 -0.1621 0.1901 0.7927
8.500 1.6026 0.01770 0.01124 -0.1591 0.1722 0.8028
9.000 1.6134 0.02029 0.01374 -0.1538 0.1373 0.8268
9.250 1.6182 0.02180 0.01522 -0.1514 0.1219 0.8416
9.500 1.6229 0.02342 0.01681 -0.1492 0.1079 0.8591
9.750 1.6270 0.02511 0.01850 -0.1471 0.0955 0.8795
10.000 1.6312 0.02669 0.02011 -0.1449 0.0860 0.9091
10.250 1.6294 0.02811 0.02159 -0.1415 0.0795 0.9999
10.500 1.6351 0.02990 0.02335 -0.1398 0.0723 0.9999
10.750 1.6425 0.03156 0.02501 -0.1384 0.0667 0.9999
11.000 1.6494 0.03326 0.02671 -0.1370 0.0621 0.9999
11.250 1.6554 0.03504 0.02850 -0.1355 0.0577 0.9999
11.500 1.6618 0.03682 0.03029 -0.1341 0.0543 0.9999
11.750 1.6674 0.03871 0.03219 -0.1327 0.0509 0.9999
12.000 1.6735 0.04057 0.03407 -0.1314 0.0482 0.9999
12.250 1.6794 0.04245 0.03597 -0.1302 0.0457 0.9999
12.500 1.6841 0.04450 0.03804 -0.1289 0.0433 0.9999
12.750 1.6909 0.04638 0.03994 -0.1278 0.0414 0.9999
13.000 1.6959 0.04847 0.04207 -0.1267 0.0395 0.9999
13.250 1.7009 0.05056 0.04418 -0.1256 0.0377 0.9999
13.500 1.7064 0.05265 0.04631 -0.1246 0.0364 0.9999
13.750 1.7117 0.05477 0.04846 -0.1236 0.0349 0.9999
14.000 1.7153 0.05712 0.05084 -0.1226 0.0335 0.9999
14.250 1.7204 0.05932 0.05308 -0.1218 0.0324 0.9999
14.500 1.7249 0.06159 0.05539 -0.1209 0.0313 0.9999
14.750 1.7282 0.06400 0.05783 -0.1201 0.0300 0.9999
15.000 1.7306 0.06654 0.06040 -0.1192 0.0287 0.9999
15.250 1.7345 0.06895 0.06286 -0.1185 0.0281 0.9999
15.500 1.7385 0.07136 0.06532 -0.1178 0.0271 0.9999
15.750 1.7406 0.07402 0.06802 -0.1172 0.0262 0.9999
16.000 1.7433 0.07657 0.07061 -0.1166 0.0254 0.9999
16.250 1.7437 0.07946 0.07354 -0.1160 0.0246 0.9999
16.500 1.7472 0.08197 0.07610 -0.1155 0.0241 0.9999
16.750 1.7488 0.08476 0.07896 -0.1151 0.0236 0.9999
17.000 1.7512 0.08745 0.08170 -0.1147 0.0230 0.9999
17.250 1.7518 0.09036 0.08466 -0.1144 0.0224 0.9999
17.500 1.7524 0.09326 0.08761 -0.1141 0.0218 0.9999
17.750 1.7521 0.09631 0.09071 -0.1138 0.0212 0.9999
18.000 1.7525 0.09932 0.09377 -0.1137 0.0208 0.9999
18.250 1.7541 0.10214 0.09665 -0.1136 0.0204 0.9999
18.500 1.7543 0.10521 0.09979 -0.1136 0.0200 0.9999
18.750 1.7553 0.10810 0.10274 -0.1137 0.0196 0.9999
19.000 1.7542 0.11135 0.10604 -0.1139 0.0191 0.9999
19.250 1.7542 0.11440 0.10914 -0.1140 0.0185 0.9999
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