EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 431 AIRFOIL (e431-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.44 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e431-il-1000000.txt Download as CSV file: xf-e431-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1189 0.09331 0.09149 -0.1074 0.9410 0.0099
-11.000 -0.1007 0.08621 0.08434 -0.1166 0.9337 0.0101
-7.000 -0.1515 0.01761 0.01236 -0.1277 0.7626 0.0077
-6.750 -0.1290 0.01639 0.01106 -0.1271 0.7589 0.0072
-6.500 -0.1076 0.01485 0.00929 -0.1263 0.7551 0.0068
-6.250 -0.0851 0.01357 0.00784 -0.1254 0.7521 0.0065
-6.000 -0.0617 0.01269 0.00685 -0.1248 0.7488 0.0063
-5.750 -0.0375 0.01205 0.00613 -0.1243 0.7454 0.0063
-5.500 -0.0130 0.01151 0.00551 -0.1239 0.7420 0.0062
-5.250 0.0122 0.01107 0.00498 -0.1237 0.7385 0.0063
-5.000 0.0378 0.01064 0.00452 -0.1234 0.7357 0.0064
-4.750 0.0638 0.01027 0.00411 -0.1233 0.7326 0.0067
-4.500 0.0902 0.00996 0.00376 -0.1232 0.7294 0.0069
-4.250 0.1170 0.00970 0.00345 -0.1232 0.7262 0.0074
-4.000 0.1440 0.00942 0.00310 -0.1232 0.7227 0.0085
-3.750 0.1712 0.00918 0.00285 -0.1232 0.7200 0.0108
-3.500 0.1980 0.00880 0.00259 -0.1233 0.7170 0.0332
-3.250 0.2254 0.00856 0.00244 -0.1234 0.7138 0.0560
-3.000 0.2528 0.00834 0.00232 -0.1237 0.7107 0.0878
-2.750 0.2803 0.00807 0.00220 -0.1240 0.7073 0.1438
-2.500 0.3070 0.00740 0.00206 -0.1246 0.7044 0.2961
-2.250 0.3339 0.00623 0.00187 -0.1257 0.7013 0.5970
-2.000 0.3624 0.00611 0.00191 -0.1259 0.6980 0.6704
-1.750 0.3911 0.00614 0.00192 -0.1261 0.6947 0.6918
-1.500 0.4199 0.00621 0.00195 -0.1264 0.6912 0.7075
-1.250 0.4484 0.00624 0.00198 -0.1266 0.6881 0.7193
-1.000 0.4772 0.00629 0.00200 -0.1268 0.6846 0.7288
-0.750 0.5054 0.00632 0.00202 -0.1270 0.6810 0.7352
-0.500 0.5339 0.00639 0.00205 -0.1271 0.6773 0.7417
-0.250 0.5622 0.00647 0.00210 -0.1273 0.6735 0.7492
0.000 0.5901 0.00653 0.00219 -0.1273 0.6698 0.7577
0.250 0.6178 0.00660 0.00225 -0.1273 0.6658 0.7659
0.500 0.6453 0.00669 0.00232 -0.1273 0.6617 0.7713
0.750 0.6735 0.00674 0.00235 -0.1275 0.6575 0.7743
1.000 0.7019 0.00676 0.00236 -0.1278 0.6533 0.7763
1.250 0.7302 0.00680 0.00237 -0.1280 0.6487 0.7781
1.500 0.7578 0.00685 0.00238 -0.1281 0.6438 0.7802
1.750 0.7857 0.00684 0.00240 -0.1283 0.6392 0.7820
2.000 0.8133 0.00687 0.00243 -0.1284 0.6339 0.7837
2.250 0.8403 0.00695 0.00247 -0.1284 0.6287 0.7857
2.500 0.8681 0.00698 0.00252 -0.1286 0.6235 0.7878
2.750 0.8954 0.00703 0.00257 -0.1286 0.6174 0.7899
3.000 0.9221 0.00711 0.00262 -0.1286 0.6117 0.7918
3.250 0.9498 0.00716 0.00267 -0.1288 0.6054 0.7936
3.500 0.9761 0.00725 0.00274 -0.1287 0.5985 0.7953
3.750 1.0027 0.00729 0.00280 -0.1286 0.5914 0.7975
4.000 1.0281 0.00738 0.00288 -0.1283 0.5832 0.7996
4.250 1.0541 0.00746 0.00297 -0.1282 0.5750 0.8017
4.750 1.1044 0.00768 0.00318 -0.1275 0.5565 0.8061
5.000 1.1289 0.00782 0.00330 -0.1271 0.5464 0.8083
5.250 1.1523 0.00799 0.00344 -0.1264 0.5351 0.8104
5.500 1.1757 0.00814 0.00357 -0.1258 0.5220 0.8126
5.750 1.1978 0.00831 0.00373 -0.1249 0.5078 0.8150
6.000 1.2186 0.00853 0.00392 -0.1238 0.4924 0.8176
6.250 1.2383 0.00878 0.00413 -0.1224 0.4759 0.8203
6.750 1.2707 0.00936 0.00460 -0.1183 0.4395 0.8260
7.000 1.2853 0.00971 0.00488 -0.1160 0.4192 0.8289
7.250 1.2986 0.01011 0.00522 -0.1135 0.3988 0.8320
7.500 1.3111 0.01056 0.00560 -0.1109 0.3784 0.8353
7.750 1.3238 0.01103 0.00600 -0.1085 0.3572 0.8388
8.000 1.3360 0.01154 0.00644 -0.1060 0.3374 0.8423
8.500 1.3571 0.01265 0.00745 -0.1006 0.2982 0.8505
8.750 1.3670 0.01329 0.00802 -0.0979 0.2786 0.8549
9.000 1.3758 0.01401 0.00867 -0.0952 0.2594 0.8592
9.250 1.3847 0.01471 0.00934 -0.0926 0.2429 0.8642
9.500 1.3923 0.01554 0.01010 -0.0899 0.2243 0.8697
9.750 1.4002 0.01641 0.01092 -0.0873 0.2064 0.8755
10.000 1.4083 0.01727 0.01176 -0.0849 0.1914 0.8824
10.250 1.4154 0.01824 0.01270 -0.0824 0.1754 0.8904
10.500 1.4228 0.01919 0.01364 -0.0801 0.1623 0.9003
10.750 1.4294 0.02017 0.01463 -0.0777 0.1502 0.9142
11.000 1.4342 0.02112 0.01566 -0.0750 0.1384 0.9572
11.250 1.4431 0.02233 0.01682 -0.0735 0.1255 1.0000
11.500 1.4511 0.02360 0.01804 -0.0719 0.1136 1.0000
11.750 1.4593 0.02488 0.01929 -0.0704 0.1027 1.0000
12.000 1.4662 0.02628 0.02065 -0.0688 0.0917 1.0000
12.250 1.4730 0.02774 0.02208 -0.0673 0.0818 1.0000
12.500 1.4795 0.02924 0.02355 -0.0658 0.0725 1.0000
12.750 1.4856 0.03082 0.02511 -0.0644 0.0643 1.0000
13.000 1.4904 0.03255 0.02680 -0.0630 0.0562 1.0000
13.250 1.4983 0.03409 0.02835 -0.0619 0.0508 1.0000
13.500 1.5042 0.03582 0.03007 -0.0608 0.0448 1.0000
13.750 1.5085 0.03773 0.03197 -0.0596 0.0391 1.0000
14.000 1.5133 0.03965 0.03390 -0.0586 0.0340 1.0000
14.250 1.5196 0.04149 0.03576 -0.0578 0.0302 1.0000
14.500 1.5242 0.04354 0.03782 -0.0569 0.0268 1.0000
14.750 1.5300 0.04551 0.03982 -0.0562 0.0242 1.0000
15.000 1.5347 0.04765 0.04200 -0.0556 0.0218 1.0000
15.250 1.5392 0.04986 0.04425 -0.0550 0.0196 1.0000
15.500 1.5438 0.05211 0.04654 -0.0545 0.0178 1.0000
15.750 1.5475 0.05451 0.04898 -0.0541 0.0160 1.0000
16.000 1.5513 0.05693 0.05145 -0.0538 0.0146 1.0000
16.250 1.5549 0.05945 0.05403 -0.0536 0.0133 1.0000
16.500 1.5560 0.06233 0.05696 -0.0535 0.0121 1.0000
16.750 1.5604 0.06485 0.05955 -0.0535 0.0111 1.0000
17.000 1.5610 0.06789 0.06264 -0.0536 0.0101 1.0000
17.250 1.5626 0.07087 0.06570 -0.0538 0.0092 1.0000
17.500 1.5641 0.07392 0.06883 -0.0541 0.0086 1.0000
17.750 1.5627 0.07742 0.07238 -0.0545 0.0076 1.0000
18.000 1.5631 0.08075 0.07580 -0.0551 0.0071 1.0000
18.250 1.5625 0.08426 0.07939 -0.0558 0.0065 1.0000
18.500 1.5598 0.08812 0.08333 -0.0566 0.0059 1.0000
18.750 1.5575 0.09201 0.08731 -0.0575 0.0055 1.0000
19.000 1.5555 0.09592 0.09130 -0.0586 0.0051 1.0000
19.250 1.5518 0.10014 0.09561 -0.0599 0.0046 1.0000
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Polar data table (+)
Polar graphs
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