E423 (e423-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E423 (e423-il) Reynolds number: 200,000 Max Cl/Cd: 73.73 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e423-il-200000.txt Download as CSV file: xf-e423-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E423
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 0.0419 0.13820 0.13453 -0.0982 0.9469 0.0301
-12.000 0.0590 0.13475 0.13108 -0.1031 0.9429 0.0305
-11.750 0.0686 0.13224 0.12857 -0.1063 0.9333 0.0306
-11.500 0.0903 0.12745 0.12378 -0.1091 0.9299 0.0308
-11.250 0.1046 0.12407 0.12039 -0.1105 0.9204 0.0312
-11.000 0.1249 0.12038 0.11668 -0.1141 0.9165 0.0318
-10.750 0.1416 0.11712 0.11341 -0.1169 0.9077 0.0325
-10.500 0.1647 0.11327 0.10952 -0.1218 0.9032 0.0333
-10.250 0.1873 0.10949 0.10571 -0.1269 0.8967 0.0344
-10.000 0.2119 0.10598 0.10213 -0.1345 0.8900 0.0350
-9.750 0.2450 0.10122 0.09731 -0.1424 0.8854 0.0353
-9.500 0.2800 0.09672 0.09273 -0.1483 0.8770 0.0362
-9.250 0.3183 0.09250 0.08840 -0.1568 0.8694 0.0372
-9.000 0.3472 0.08898 0.08477 -0.1633 0.8571 0.0389
-8.750 0.3659 0.08665 0.08231 -0.1700 0.8429 0.0400
-8.500 0.3860 0.08354 0.07908 -0.1735 0.8315 0.0404
-8.250 0.4048 0.08082 0.07627 -0.1743 0.8201 0.0412
-8.000 0.4178 0.07889 0.07427 -0.1752 0.8091 0.0419
-7.750 0.4309 0.07695 0.07223 -0.1765 0.7995 0.0429
-7.500 0.4373 0.07532 0.07058 -0.1767 0.7898 0.0444
-7.250 0.4311 0.07475 0.06995 -0.1791 0.7806 0.0456
-7.000 0.4393 0.07253 0.06774 -0.1784 0.7730 0.0459
-6.750 0.4582 0.06992 0.06508 -0.1776 0.7666 0.0468
-6.500 0.4720 0.06807 0.06315 -0.1783 0.7608 0.0485
-6.250 0.4734 0.06678 0.06191 -0.1769 0.7535 0.0497
-6.000 0.4692 0.06592 0.06105 -0.1772 0.7469 0.0515
-5.750 0.4762 0.06390 0.05900 -0.1804 0.7417 0.0523
-5.500 0.4868 0.06202 0.05715 -0.1775 0.7364 0.0531
-5.250 0.4983 0.06042 0.05554 -0.1772 0.7312 0.0546
-4.750 0.5252 0.05624 0.05131 -0.1841 0.7218 0.0599
-4.500 0.5354 0.05509 0.05019 -0.1814 0.7167 0.0627
-4.250 0.5661 0.05170 0.04672 -0.1937 0.7119 0.0674
-4.000 0.5793 0.05000 0.04499 -0.1910 0.7084 0.0684
-3.750 0.5989 0.04836 0.04331 -0.1917 0.7048 0.0704
-3.500 0.6469 0.03885 0.03361 -0.2094 0.7003 0.0515
-3.250 0.6639 0.03895 0.03373 -0.2076 0.6959 0.0563
-3.000 0.6905 0.03852 0.03324 -0.2089 0.6921 0.0706
-2.750 0.8037 0.01985 0.01232 -0.2406 0.6897 0.0687
-2.500 0.8331 0.01972 0.01207 -0.2411 0.6864 0.0777
-2.250 0.8564 0.01975 0.01206 -0.2403 0.6822 0.0860
-2.000 0.8824 0.01965 0.01199 -0.2400 0.6781 0.0939
-1.750 0.9117 0.01940 0.01161 -0.2404 0.6745 0.1031
-1.500 0.9433 0.01920 0.01121 -0.2411 0.6714 0.1138
-1.250 0.9725 0.01934 0.01129 -0.2414 0.6684 0.1242
-1.000 0.9942 0.01933 0.01135 -0.2403 0.6644 0.1333
-0.750 1.0196 0.01932 0.01123 -0.2399 0.6604 0.1446
-0.500 1.0470 0.01940 0.01130 -0.2398 0.6569 0.1557
-0.250 1.0771 0.01937 0.01120 -0.2403 0.6540 0.1670
0.000 1.1095 0.01946 0.01110 -0.2412 0.6513 0.1796
0.250 1.1294 0.01959 0.01135 -0.2398 0.6474 0.1889
0.500 1.1525 0.01966 0.01140 -0.2390 0.6434 0.1995
0.750 1.1783 0.01975 0.01148 -0.2387 0.6400 0.2109
1.000 1.2072 0.01975 0.01145 -0.2390 0.6370 0.2221
1.250 1.2389 0.01981 0.01140 -0.2398 0.6343 0.2352
1.500 1.2628 0.02002 0.01166 -0.2392 0.6309 0.2468
1.750 1.2825 0.02020 0.01194 -0.2378 0.6268 0.2578
2.000 1.3064 0.02036 0.01212 -0.2371 0.6233 0.2712
2.250 1.3335 0.02046 0.01222 -0.2371 0.6201 0.2864
2.500 1.3643 0.02050 0.01224 -0.2377 0.6172 0.3043
2.750 1.3947 0.02067 0.01243 -0.2384 0.6144 0.3249
3.000 1.4098 0.02098 0.01293 -0.2362 0.6103 0.3450
3.250 1.4309 0.02117 0.01326 -0.2351 0.6064 0.3755
3.500 1.4571 0.02113 0.01345 -0.2350 0.6029 0.4533
3.750 1.4822 0.02060 0.01348 -0.2344 0.6001 1.0000
4.000 1.5154 0.02086 0.01359 -0.2355 0.5975 1.0000
4.250 1.5294 0.02138 0.01417 -0.2331 0.5933 1.0000
4.500 1.5469 0.02179 0.01461 -0.2314 0.5890 1.0000
4.750 1.5710 0.02205 0.01484 -0.2308 0.5854 1.0000
5.000 1.6003 0.02221 0.01494 -0.2312 0.5824 1.0000
5.250 1.6350 0.02240 0.01501 -0.2326 0.5797 1.0000
5.500 1.6441 0.02300 0.01574 -0.2294 0.5751 1.0000
5.750 1.6599 0.02342 0.01621 -0.2274 0.5706 1.0000
6.000 1.6846 0.02359 0.01638 -0.2269 0.5668 1.0000
6.250 1.7173 0.02363 0.01635 -0.2279 0.5636 1.0000
6.500 1.7416 0.02397 0.01668 -0.2275 0.5599 1.0000
6.750 1.7464 0.02456 0.01742 -0.2235 0.5545 1.0000
7.000 1.7670 0.02476 0.01764 -0.2223 0.5502 1.0000
7.250 1.7990 0.02472 0.01755 -0.2232 0.5466 1.0000
7.500 1.8271 0.02492 0.01774 -0.2235 0.5429 1.0000
7.750 1.8247 0.02560 0.01859 -0.2182 0.5372 1.0000
8.000 1.8428 0.02579 0.01881 -0.2166 0.5326 1.0000
8.250 1.8774 0.02566 0.01861 -0.2179 0.5289 1.0000
8.500 1.8897 0.02607 0.01911 -0.2153 0.5242 1.0000
8.750 1.8849 0.02668 0.01984 -0.2096 0.5186 1.0000
9.000 1.9077 0.02669 0.01985 -0.2088 0.5140 1.0000
9.250 1.9493 0.02644 0.01952 -0.2115 0.5098 1.0000
9.500 1.9249 0.02756 0.02087 -0.2026 0.5037 1.0000
9.750 1.9379 0.02781 0.02116 -0.2002 0.4984 1.0000
10.000 1.9762 0.02745 0.02072 -0.2021 0.4938 1.0000
10.250 1.9546 0.02879 0.02227 -0.1942 0.4874 1.0000
10.500 1.9655 0.02917 0.02270 -0.1917 0.4816 1.0000
10.750 1.9965 0.02895 0.02242 -0.1923 0.4764 1.0000
11.000 1.9729 0.03070 0.02438 -0.1849 0.4693 1.0000
11.250 1.9901 0.03090 0.02458 -0.1835 0.4632 1.0000
11.500 1.9884 0.03207 0.02585 -0.1797 0.4564 1.0000
11.750 1.9867 0.03326 0.02713 -0.1760 0.4491 1.0000
12.000 2.0015 0.03374 0.02760 -0.1745 0.4424 1.0000
12.250 1.9857 0.03595 0.02996 -0.1696 0.4341 1.0000
12.500 2.0035 0.03629 0.03027 -0.1686 0.4270 1.0000
12.750 1.9833 0.03915 0.03329 -0.1638 0.4179 1.0000
13.000 1.9930 0.04009 0.03423 -0.1622 0.4098 1.0000
13.250 1.9798 0.04286 0.03711 -0.1587 0.4002 1.0000
13.500 1.9779 0.04493 0.03923 -0.1564 0.3910 1.0000
13.750 1.9804 0.04665 0.04094 -0.1545 0.3814 1.0000
14.000 1.9650 0.05021 0.04462 -0.1517 0.3708 1.0000
14.250 1.9666 0.05223 0.04664 -0.1500 0.3608 1.0000
14.500 1.9612 0.05504 0.04947 -0.1482 0.3499 1.0000
14.750 1.9495 0.05870 0.05321 -0.1463 0.3387 1.0000
15.000 1.9465 0.06147 0.05599 -0.1448 0.3278 1.0000
15.250 1.9447 0.06414 0.05861 -0.1435 0.3168 1.0000
15.500 1.9322 0.06828 0.06285 -0.1422 0.3053 1.0000
15.750 1.9258 0.07174 0.06633 -0.1411 0.2943 1.0000
16.000 1.9239 0.07463 0.06916 -0.1401 0.2836 1.0000
16.250 1.9144 0.07866 0.07325 -0.1393 0.2726 1.0000
16.500 1.9075 0.08243 0.07707 -0.1386 0.2622 1.0000
16.750 1.9052 0.08554 0.08011 -0.1380 0.2522 1.0000
17.000 1.8969 0.08962 0.08426 -0.1375 0.2421 1.0000
17.250 1.8915 0.09331 0.08799 -0.1372 0.2326 1.0000
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Polar data table (+)
Polar graphs
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