EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 435 AIRFOIL (e435-il) Reynolds number: 500,000 Max Cl/Cd: 111.77 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e435-il-500000-n5.txt Download as CSV file: xf-e435-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 435 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2947 0.05501 0.05209 -0.1337 0.9291 0.0056
-11.750 -0.3014 0.04365 0.04030 -0.1502 0.9160 0.0055
-11.500 -0.3010 0.03757 0.03382 -0.1588 0.8966 0.0055
-11.250 -0.3075 0.03375 0.02964 -0.1613 0.8760 0.0055
-11.000 -0.3112 0.03130 0.02694 -0.1614 0.8602 0.0054
-10.750 -0.3144 0.02922 0.02461 -0.1605 0.8470 0.0054
-10.500 -0.3213 0.02696 0.02205 -0.1587 0.8349 0.0055
-10.250 -0.3206 0.02552 0.02042 -0.1568 0.8255 0.0054
-10.000 -0.3208 0.02421 0.01889 -0.1544 0.8174 0.0055
-9.750 -0.3147 0.02306 0.01758 -0.1527 0.8104 0.0054
-9.500 -0.3041 0.02185 0.01615 -0.1513 0.8041 0.0055
-9.250 -0.2904 0.02078 0.01490 -0.1501 0.7987 0.0055
-9.000 -0.2743 0.01987 0.01385 -0.1491 0.7932 0.0055
-8.750 -0.2568 0.01901 0.01284 -0.1482 0.7885 0.0056
-8.500 -0.2379 0.01823 0.01191 -0.1475 0.7843 0.0056
-8.250 -0.2184 0.01747 0.01106 -0.1468 0.7799 0.0057
-8.000 -0.1977 0.01683 0.01032 -0.1462 0.7755 0.0057
-7.750 -0.1772 0.01611 0.00949 -0.1456 0.7714 0.0058
-7.500 -0.1554 0.01548 0.00877 -0.1453 0.7679 0.0059
-7.250 -0.1330 0.01488 0.00812 -0.1449 0.7643 0.0061
-7.000 -0.1094 0.01439 0.00757 -0.1447 0.7604 0.0063
-6.750 -0.0851 0.01396 0.00708 -0.1445 0.7567 0.0065
-6.500 -0.0600 0.01357 0.00662 -0.1445 0.7534 0.0068
-6.250 -0.0345 0.01319 0.00617 -0.1445 0.7504 0.0073
-6.000 -0.0086 0.01284 0.00578 -0.1445 0.7470 0.0077
-5.750 0.0174 0.01247 0.00537 -0.1446 0.7435 0.0085
-5.500 0.0440 0.01218 0.00502 -0.1447 0.7402 0.0096
-5.250 0.0711 0.01190 0.00470 -0.1450 0.7373 0.0113
-5.000 0.0984 0.01163 0.00441 -0.1452 0.7344 0.0148
-4.750 0.1257 0.01135 0.00416 -0.1455 0.7311 0.0217
-4.500 0.1532 0.01108 0.00394 -0.1458 0.7278 0.0338
-4.250 0.1810 0.01080 0.00373 -0.1463 0.7247 0.0535
-4.000 0.2091 0.01049 0.00351 -0.1468 0.7217 0.0837
-3.750 0.2376 0.01015 0.00331 -0.1475 0.7188 0.1306
-3.500 0.2662 0.00970 0.00312 -0.1483 0.7157 0.2000
-3.250 0.2954 0.00918 0.00289 -0.1494 0.7124 0.2949
-3.000 0.3256 0.00853 0.00267 -0.1508 0.7091 0.4289
-2.750 0.3552 0.00832 0.00268 -0.1515 0.7061 0.5220
-2.250 0.4130 0.00835 0.00272 -0.1522 0.7001 0.5678
-2.000 0.4416 0.00838 0.00272 -0.1524 0.6966 0.5795
-1.750 0.4703 0.00843 0.00272 -0.1527 0.6932 0.5906
-1.500 0.4987 0.00850 0.00278 -0.1528 0.6899 0.6036
-1.250 0.5273 0.00859 0.00284 -0.1530 0.6869 0.6150
-1.000 0.5556 0.00864 0.00287 -0.1532 0.6833 0.6227
-0.750 0.5840 0.00867 0.00287 -0.1534 0.6795 0.6261
-0.500 0.6120 0.00869 0.00288 -0.1536 0.6757 0.6284
-0.250 0.6402 0.00874 0.00288 -0.1538 0.6721 0.6308
0.000 0.6683 0.00877 0.00290 -0.1539 0.6683 0.6333
0.250 0.6962 0.00880 0.00292 -0.1541 0.6639 0.6356
0.500 0.7240 0.00885 0.00293 -0.1542 0.6595 0.6381
0.750 0.7519 0.00891 0.00294 -0.1544 0.6555 0.6407
1.000 0.7795 0.00894 0.00299 -0.1545 0.6510 0.6429
1.250 0.8066 0.00898 0.00303 -0.1545 0.6459 0.6449
1.500 0.8336 0.00904 0.00308 -0.1544 0.6408 0.6470
1.750 0.8606 0.00909 0.00314 -0.1544 0.6356 0.6493
2.000 0.8873 0.00915 0.00320 -0.1544 0.6297 0.6517
2.250 0.9139 0.00924 0.00325 -0.1542 0.6242 0.6544
2.500 0.9405 0.00931 0.00333 -0.1542 0.6184 0.6571
2.750 0.9666 0.00938 0.00341 -0.1540 0.6119 0.6595
3.000 0.9922 0.00947 0.00349 -0.1537 0.6055 0.6616
3.250 1.0176 0.00955 0.00360 -0.1534 0.5979 0.6639
3.500 1.0423 0.00967 0.00371 -0.1529 0.5905 0.6664
3.750 1.0672 0.00977 0.00382 -0.1525 0.5820 0.6690
4.000 1.0912 0.00990 0.00394 -0.1519 0.5736 0.6718
4.250 1.1148 0.01004 0.00408 -0.1513 0.5639 0.6746
4.500 1.1377 0.01019 0.00423 -0.1505 0.5538 0.6773
4.750 1.1590 0.01037 0.00440 -0.1494 0.5429 0.6800
5.000 1.1797 0.01056 0.00459 -0.1482 0.5304 0.6828
5.250 1.1992 0.01075 0.00477 -0.1467 0.5180 0.6858
5.500 1.2167 0.01098 0.00498 -0.1449 0.5048 0.6889
5.750 1.2332 0.01125 0.00523 -0.1429 0.4909 0.6919
6.000 1.2491 0.01157 0.00552 -0.1408 0.4757 0.6946
6.250 1.2637 0.01194 0.00586 -0.1385 0.4589 0.6976
6.500 1.2775 0.01236 0.00624 -0.1362 0.4412 0.7011
6.750 1.2900 0.01284 0.00667 -0.1336 0.4228 0.7050
7.000 1.3012 0.01339 0.00716 -0.1309 0.4036 0.7087
7.500 1.3230 0.01457 0.00827 -0.1257 0.3676 0.7157
7.750 1.3334 0.01525 0.00890 -0.1231 0.3490 0.7197
8.000 1.3436 0.01596 0.00957 -0.1207 0.3316 0.7238
8.250 1.3533 0.01673 0.01031 -0.1182 0.3147 0.7277
8.500 1.3627 0.01755 0.01111 -0.1158 0.2982 0.7320
8.750 1.3717 0.01845 0.01197 -0.1134 0.2816 0.7370
9.000 1.3804 0.01941 0.01289 -0.1111 0.2651 0.7422
9.250 1.3889 0.02041 0.01387 -0.1089 0.2493 0.7472
9.500 1.3970 0.02148 0.01493 -0.1067 0.2335 0.7530
9.750 1.4048 0.02263 0.01605 -0.1046 0.2181 0.7588
10.000 1.4122 0.02384 0.01724 -0.1026 0.2026 0.7648
10.250 1.4199 0.02508 0.01846 -0.1007 0.1883 0.7717
10.500 1.4282 0.02632 0.01970 -0.0989 0.1758 0.7789
10.750 1.4354 0.02766 0.02104 -0.0971 0.1628 0.7876
11.000 1.4422 0.02907 0.02246 -0.0954 0.1498 0.7973
11.500 1.4550 0.03205 0.02546 -0.0921 0.1264 0.8224
12.000 1.4686 0.03495 0.02848 -0.0889 0.1069 0.8682
12.250 1.4708 0.03638 0.03003 -0.0867 0.0987 1.0000
12.500 1.4775 0.03814 0.03177 -0.0856 0.0897 1.0000
12.750 1.4848 0.03989 0.03352 -0.0845 0.0819 1.0000
13.000 1.4907 0.04181 0.03543 -0.0835 0.0744 1.0000
13.250 1.4963 0.04379 0.03741 -0.0826 0.0672 1.0000
13.500 1.5026 0.04575 0.03940 -0.0817 0.0610 1.0000
13.750 1.5078 0.04786 0.04152 -0.0809 0.0551 1.0000
14.000 1.5126 0.05008 0.04375 -0.0802 0.0496 1.0000
14.250 1.5183 0.05225 0.04596 -0.0796 0.0451 1.0000
14.500 1.5222 0.05465 0.04838 -0.0790 0.0410 1.0000
14.750 1.5274 0.05695 0.05074 -0.0785 0.0374 1.0000
15.000 1.5310 0.05951 0.05333 -0.0781 0.0340 1.0000
15.250 1.5349 0.06206 0.05594 -0.0778 0.0309 1.0000
15.500 1.5377 0.06482 0.05874 -0.0775 0.0281 1.0000
15.750 1.5409 0.06756 0.06154 -0.0774 0.0256 1.0000
16.000 1.5422 0.07059 0.06462 -0.0773 0.0230 1.0000
16.250 1.5444 0.07357 0.06767 -0.0774 0.0211 1.0000
16.500 1.5457 0.07673 0.07090 -0.0776 0.0193 1.0000
16.750 1.5461 0.08006 0.07429 -0.0778 0.0173 1.0000
17.000 1.5463 0.08348 0.07778 -0.0782 0.0156 1.0000
17.250 1.5464 0.08696 0.08133 -0.0787 0.0143 1.0000
17.500 1.5454 0.09065 0.08511 -0.0794 0.0130 1.0000
17.750 1.5445 0.09440 0.08894 -0.0801 0.0118 1.0000
18.000 1.5422 0.09841 0.09302 -0.0811 0.0108 1.0000
18.250 1.5414 0.10221 0.09693 -0.0820 0.0099 1.0000
18.500 1.5392 0.10626 0.10107 -0.0832 0.0092 1.0000
18.750 1.5359 0.11056 0.10545 -0.0845 0.0086 1.0000
19.000 1.5338 0.11469 0.10970 -0.0859 0.0081 1.0000
19.250 1.5309 0.11898 0.11409 -0.0875 0.0075 1.0000
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