EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 431 AIRFOIL (e431-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.18 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e431-il-1000000-n5.txt Download as CSV file: xf-e431-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 431 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2500 0.04219 0.03939 -0.1466 0.7974 0.0034
-10.250 -0.3320 0.03095 0.02755 -0.1427 0.7786 0.0033
-9.750 -0.3643 0.02558 0.02160 -0.1345 0.7655 0.0033
-9.500 -0.3610 0.02357 0.01933 -0.1322 0.7606 0.0033
-9.250 -0.3535 0.02173 0.01721 -0.1301 0.7559 0.0033
-9.000 -0.3418 0.02006 0.01529 -0.1285 0.7519 0.0033
-8.750 -0.3257 0.01878 0.01380 -0.1273 0.7478 0.0032
-8.500 -0.3083 0.01756 0.01238 -0.1262 0.7440 0.0033
-8.250 -0.2886 0.01662 0.01127 -0.1253 0.7404 0.0032
-8.000 -0.2678 0.01574 0.01023 -0.1246 0.7372 0.0033
-7.750 -0.2456 0.01498 0.00935 -0.1240 0.7339 0.0033
-7.500 -0.2231 0.01426 0.00850 -0.1234 0.7304 0.0033
-7.250 -0.1997 0.01368 0.00783 -0.1229 0.7271 0.0033
-7.000 -0.1764 0.01310 0.00714 -0.1224 0.7240 0.0033
-6.750 -0.1520 0.01263 0.00660 -0.1221 0.7210 0.0033
-6.500 -0.1272 0.01216 0.00605 -0.1218 0.7181 0.0034
-6.250 -0.1022 0.01172 0.00555 -0.1216 0.7149 0.0034
-6.000 -0.0768 0.01135 0.00512 -0.1214 0.7118 0.0034
-5.750 -0.0512 0.01103 0.00475 -0.1212 0.7087 0.0035
-5.500 -0.0253 0.01074 0.00440 -0.1210 0.7058 0.0035
-5.250 0.0012 0.01042 0.00404 -0.1210 0.7031 0.0036
-5.000 0.0275 0.01008 0.00366 -0.1209 0.7002 0.0038
-4.750 0.0543 0.00983 0.00338 -0.1209 0.6970 0.0042
-4.500 0.0813 0.00965 0.00317 -0.1209 0.6939 0.0044
-4.250 0.1082 0.00949 0.00296 -0.1210 0.6909 0.0050
-4.000 0.1359 0.00931 0.00277 -0.1211 0.6882 0.0058
-3.750 0.1636 0.00914 0.00260 -0.1213 0.6852 0.0071
-3.500 0.1912 0.00898 0.00245 -0.1214 0.6819 0.0106
-3.250 0.2186 0.00882 0.00231 -0.1215 0.6787 0.0176
-3.000 0.2460 0.00868 0.00219 -0.1217 0.6756 0.0284
-2.750 0.2739 0.00851 0.00208 -0.1219 0.6727 0.0464
-2.500 0.3015 0.00820 0.00197 -0.1222 0.6696 0.0952
-2.250 0.3289 0.00784 0.00186 -0.1226 0.6660 0.1716
-2.000 0.3566 0.00754 0.00177 -0.1230 0.6626 0.2484
-1.500 0.4130 0.00680 0.00159 -0.1242 0.6559 0.4496
-1.250 0.4418 0.00626 0.00153 -0.1251 0.6520 0.6147
-1.000 0.4702 0.00620 0.00157 -0.1253 0.6480 0.6612
-0.750 0.4983 0.00624 0.00158 -0.1255 0.6439 0.6789
-0.500 0.5270 0.00625 0.00161 -0.1258 0.6400 0.6915
-0.250 0.5554 0.00628 0.00164 -0.1260 0.6355 0.7055
0.000 0.5832 0.00634 0.00170 -0.1261 0.6307 0.7205
0.250 0.6112 0.00641 0.00176 -0.1262 0.6263 0.7330
0.500 0.6394 0.00646 0.00181 -0.1263 0.6213 0.7395
0.750 0.6672 0.00652 0.00183 -0.1265 0.6157 0.7419
1.000 0.6950 0.00659 0.00185 -0.1266 0.6106 0.7439
1.250 0.7232 0.00664 0.00188 -0.1269 0.6048 0.7456
1.500 0.7502 0.00671 0.00192 -0.1268 0.5984 0.7474
1.750 0.7778 0.00676 0.00197 -0.1270 0.5920 0.7493
2.000 0.8047 0.00684 0.00203 -0.1269 0.5847 0.7513
2.250 0.8317 0.00692 0.00209 -0.1269 0.5779 0.7531
2.500 0.8585 0.00701 0.00215 -0.1269 0.5699 0.7550
2.750 0.8850 0.00711 0.00223 -0.1268 0.5619 0.7569
3.000 0.9111 0.00722 0.00231 -0.1267 0.5529 0.7588
3.250 0.9373 0.00733 0.00239 -0.1266 0.5438 0.7606
3.500 0.9625 0.00747 0.00249 -0.1262 0.5334 0.7625
3.750 0.9872 0.00761 0.00261 -0.1258 0.5212 0.7645
4.000 1.0115 0.00777 0.00274 -0.1253 0.5079 0.7665
4.250 1.0350 0.00796 0.00289 -0.1247 0.4935 0.7684
4.500 1.0580 0.00816 0.00305 -0.1240 0.4787 0.7704
4.750 1.0800 0.00840 0.00323 -0.1231 0.4624 0.7725
5.000 1.1014 0.00865 0.00342 -0.1221 0.4459 0.7747
5.250 1.1219 0.00893 0.00363 -0.1209 0.4286 0.7768
5.500 1.1404 0.00924 0.00386 -0.1193 0.4103 0.7790
5.750 1.1572 0.00952 0.00410 -0.1174 0.3919 0.7814
6.000 1.1729 0.00986 0.00437 -0.1153 0.3726 0.7838
6.250 1.1887 0.01022 0.00468 -0.1132 0.3543 0.7863
6.500 1.2039 0.01062 0.00500 -0.1111 0.3362 0.7888
7.000 1.2328 0.01149 0.00574 -0.1068 0.2997 0.7939
7.250 1.2470 0.01195 0.00614 -0.1047 0.2827 0.7963
7.500 1.2607 0.01242 0.00657 -0.1025 0.2664 0.7991
7.750 1.2726 0.01298 0.00706 -0.1001 0.2478 0.8022
8.000 1.2852 0.01353 0.00757 -0.0978 0.2324 0.8055
8.250 1.2967 0.01415 0.00813 -0.0955 0.2162 0.8087
8.750 1.3197 0.01546 0.00937 -0.0911 0.1874 0.8146
9.000 1.3300 0.01621 0.01008 -0.0889 0.1731 0.8181
9.250 1.3398 0.01703 0.01086 -0.0866 0.1588 0.8218
9.500 1.3509 0.01783 0.01163 -0.0847 0.1474 0.8255
9.750 1.3597 0.01877 0.01253 -0.0825 0.1335 0.8294
10.000 1.3695 0.01969 0.01344 -0.0806 0.1225 0.8338
10.250 1.3777 0.02074 0.01446 -0.0785 0.1098 0.8386
10.500 1.3868 0.02180 0.01548 -0.0767 0.0998 0.8429
10.750 1.3967 0.02280 0.01650 -0.0750 0.0911 0.8478
11.000 1.4069 0.02384 0.01755 -0.0734 0.0835 0.8533
11.500 1.4236 0.02623 0.01995 -0.0701 0.0679 0.8657
11.750 1.4328 0.02741 0.02115 -0.0687 0.0613 0.8736
12.000 1.4395 0.02876 0.02253 -0.0670 0.0543 0.8839
12.500 1.4515 0.03147 0.02533 -0.0635 0.0421 0.9210
13.000 1.4662 0.03449 0.02843 -0.0613 0.0326 1.0000
13.500 1.4820 0.03769 0.03166 -0.0594 0.0260 1.0000
13.750 1.4881 0.03950 0.03348 -0.0584 0.0223 1.0000
14.000 1.4938 0.04140 0.03540 -0.0575 0.0191 1.0000
14.250 1.5007 0.04324 0.03727 -0.0568 0.0167 1.0000
14.500 1.5065 0.04521 0.03927 -0.0561 0.0146 1.0000
14.750 1.5131 0.04715 0.04126 -0.0555 0.0133 1.0000
15.000 1.5191 0.04921 0.04335 -0.0550 0.0120 1.0000
15.250 1.5249 0.05132 0.04552 -0.0546 0.0108 1.0000
15.500 1.5297 0.05359 0.04784 -0.0542 0.0098 1.0000
15.750 1.5349 0.05586 0.05016 -0.0539 0.0087 1.0000
16.000 1.5383 0.05837 0.05273 -0.0536 0.0078 1.0000
16.250 1.5426 0.06083 0.05525 -0.0535 0.0070 1.0000
16.500 1.5460 0.06348 0.05796 -0.0535 0.0062 1.0000
16.750 1.5480 0.06633 0.06087 -0.0535 0.0055 1.0000
17.000 1.5504 0.06917 0.06377 -0.0536 0.0048 1.0000
17.250 1.5507 0.07234 0.06701 -0.0539 0.0041 1.0000
17.500 1.5524 0.07541 0.07017 -0.0543 0.0039 1.0000
17.750 1.5520 0.07882 0.07365 -0.0547 0.0033 1.0000
18.000 1.5513 0.08233 0.07723 -0.0554 0.0029 1.0000
18.250 1.5510 0.08583 0.08082 -0.0561 0.0027 1.0000
18.500 1.5496 0.08955 0.08463 -0.0569 0.0025 1.0000
18.750 1.5478 0.09340 0.08857 -0.0579 0.0023 1.0000
19.000 1.5447 0.09751 0.09277 -0.0591 0.0020 1.0000
19.250 1.5413 0.10170 0.09704 -0.0604 0.0019 1.0000
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