EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 50,000 Max Cl/Cd: 29.94 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e403-il-50000-n5.txt Download as CSV file: xf-e403-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 403 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5073 0.11207 0.10519 -0.0485 1.0000 0.0419
-10.750 -0.5273 0.10433 0.09750 -0.0516 1.0000 0.0409
-10.500 -0.5588 0.09603 0.08921 -0.0552 1.0000 0.0398
-10.250 -0.6134 0.08752 0.08055 -0.0587 1.0000 0.0385
-10.000 -0.6451 0.08345 0.07632 -0.0584 1.0000 0.0380
-9.750 -0.6669 0.08028 0.07311 -0.0570 1.0000 0.0379
-9.500 -0.6909 0.07757 0.07034 -0.0547 1.0000 0.0378
-9.250 -0.7125 0.07487 0.06756 -0.0525 1.0000 0.0377
-9.000 -0.7283 0.07170 0.06425 -0.0510 1.0000 0.0375
-8.750 -0.7399 0.06844 0.06078 -0.0495 1.0000 0.0375
-8.500 -0.7474 0.06508 0.05717 -0.0482 1.0000 0.0374
-8.250 -0.7501 0.06171 0.05351 -0.0470 1.0000 0.0374
-8.000 -0.7482 0.05843 0.04990 -0.0460 1.0000 0.0374
-7.750 -0.7420 0.05531 0.04640 -0.0452 1.0000 0.0375
-7.500 -0.7322 0.05240 0.04304 -0.0444 1.0000 0.0379
-7.250 -0.7196 0.04973 0.04020 -0.0437 1.0000 0.0389
-7.000 -0.7049 0.04764 0.03795 -0.0430 1.0000 0.0402
-6.750 -0.6884 0.04571 0.03579 -0.0421 1.0000 0.0416
-6.500 -0.6706 0.04386 0.03369 -0.0410 1.0000 0.0431
-6.250 -0.6518 0.04223 0.03183 -0.0395 1.0000 0.0441
-6.000 -0.6330 0.04091 0.03030 -0.0375 1.0000 0.0453
-5.750 -0.6145 0.03988 0.02908 -0.0351 1.0000 0.0467
-5.500 -0.5975 0.03900 0.02811 -0.0324 1.0000 0.0484
-5.250 -0.5817 0.03806 0.02717 -0.0306 1.0000 0.0514
-5.000 -0.5651 0.03719 0.02619 -0.0291 1.0000 0.0558
-4.750 -0.5412 0.03623 0.02516 -0.0294 0.9974 0.0615
-4.500 -0.5138 0.03518 0.02399 -0.0306 0.9944 0.0705
-4.250 -0.4856 0.03351 0.02251 -0.0330 0.9912 0.0938
-4.000 -0.4584 0.02980 0.02136 -0.0375 0.9893 0.3814
-3.750 -0.4420 0.03296 0.02493 -0.0314 0.9844 0.5767
-3.500 -0.4291 0.03542 0.02726 -0.0252 0.9789 0.6235
-3.250 -0.4126 0.03727 0.02891 -0.0203 0.9742 0.6542
-3.000 -0.3963 0.03821 0.02966 -0.0164 0.9692 0.6735
-2.750 -0.3739 0.03853 0.02975 -0.0151 0.9644 0.6879
-2.500 -0.3424 0.03860 0.02948 -0.0169 0.9603 0.6993
-2.250 -0.3209 0.03856 0.02925 -0.0158 0.9552 0.7058
-2.000 -0.2894 0.03837 0.02879 -0.0182 0.9503 0.7144
-1.750 -0.2606 0.03848 0.02871 -0.0188 0.9459 0.7193
-1.500 -0.2353 0.03828 0.02831 -0.0194 0.9400 0.7253
-1.250 -0.2032 0.03819 0.02802 -0.0217 0.9348 0.7310
-1.000 -0.1727 0.03829 0.02794 -0.0229 0.9300 0.7354
-0.750 -0.1473 0.03812 0.02765 -0.0236 0.9233 0.7403
-0.500 -0.1109 0.03817 0.02753 -0.0268 0.9182 0.7456
-0.250 -0.0858 0.03814 0.02741 -0.0270 0.9117 0.7491
0.000 -0.0565 0.03815 0.02731 -0.0282 0.9052 0.7533
0.250 -0.0211 0.03826 0.02731 -0.0309 0.8998 0.7579
0.500 0.0059 0.03821 0.02719 -0.0319 0.8919 0.7619
0.750 0.0402 0.03834 0.02726 -0.0338 0.8865 0.7655
1.000 0.0636 0.03829 0.02718 -0.0340 0.8775 0.7694
1.250 0.1029 0.03844 0.02726 -0.0371 0.8719 0.7737
1.500 0.1281 0.03843 0.02724 -0.0378 0.8625 0.7773
1.750 0.1641 0.03850 0.02730 -0.0398 0.8566 0.7808
2.000 0.1882 0.03849 0.02731 -0.0401 0.8465 0.7847
2.250 0.2207 0.03854 0.02737 -0.0419 0.8381 0.7886
2.500 0.2556 0.03855 0.02741 -0.0439 0.8300 0.7923
2.750 0.2802 0.03853 0.02744 -0.0440 0.8196 0.7957
3.000 0.3153 0.03846 0.02742 -0.0457 0.8118 0.7997
3.250 0.3457 0.03844 0.02746 -0.0470 0.8014 0.8036
3.500 0.3739 0.03845 0.02756 -0.0479 0.7901 0.8074
3.750 0.4037 0.03830 0.02751 -0.0485 0.7801 0.8110
4.000 0.4373 0.03810 0.02741 -0.0497 0.7707 0.8150
4.250 0.4651 0.03808 0.02752 -0.0504 0.7581 0.8192
4.500 0.4935 0.03799 0.02755 -0.0509 0.7456 0.8230
4.750 0.5222 0.03776 0.02746 -0.0512 0.7338 0.8270
5.000 0.5605 0.03719 0.02708 -0.0526 0.7247 0.8313
5.250 0.5903 0.03699 0.02703 -0.0532 0.7106 0.8358
5.500 0.6173 0.03665 0.02686 -0.0529 0.6964 0.8399
5.750 0.6460 0.03621 0.02662 -0.0528 0.6821 0.8444
6.000 0.6774 0.03570 0.02630 -0.0531 0.6674 0.8492
6.250 0.7081 0.03512 0.02592 -0.0530 0.6522 0.8539
6.500 0.7392 0.03443 0.02546 -0.0528 0.6361 0.8591
6.750 0.7746 0.03365 0.02488 -0.0531 0.6187 0.8643
7.000 0.8065 0.03298 0.02439 -0.0529 0.5982 0.8696
7.250 0.8374 0.03241 0.02401 -0.0526 0.5740 0.8754
7.500 0.8709 0.03189 0.02361 -0.0527 0.5462 0.8814
7.750 0.8998 0.03152 0.02332 -0.0520 0.5160 0.8877
8.000 0.9267 0.03153 0.02338 -0.0515 0.4825 0.8946
8.250 0.9476 0.03177 0.02363 -0.0502 0.4497 0.9019
8.500 0.9665 0.03228 0.02414 -0.0489 0.4164 0.9103
8.750 0.9808 0.03293 0.02480 -0.0471 0.3840 0.9201
9.000 0.9932 0.03375 0.02564 -0.0453 0.3517 0.9319
9.250 1.0039 0.03473 0.02661 -0.0435 0.3196 0.9488
9.500 1.0123 0.03580 0.02767 -0.0419 0.2878 1.0000
9.750 1.0236 0.03746 0.02927 -0.0412 0.2543 1.0000
10.000 1.0336 0.03932 0.03107 -0.0406 0.2220 1.0000
10.250 1.0422 0.04138 0.03309 -0.0399 0.1915 1.0000
10.500 1.0479 0.04372 0.03534 -0.0393 0.1607 1.0000
10.750 1.0512 0.04634 0.03783 -0.0387 0.1310 1.0000
11.000 1.0540 0.04917 0.04050 -0.0384 0.1066 1.0000
11.250 1.0585 0.05206 0.04337 -0.0380 0.0878 1.0000
11.500 1.0625 0.05508 0.04639 -0.0377 0.0748 1.0000
11.750 1.0680 0.05808 0.04944 -0.0374 0.0660 1.0000
12.000 1.0722 0.06114 0.05250 -0.0373 0.0600 1.0000
12.250 1.0819 0.06392 0.05554 -0.0371 0.0540 1.0000
12.500 1.0880 0.06689 0.05855 -0.0371 0.0504 1.0000
12.750 1.1011 0.06962 0.06150 -0.0369 0.0474 1.0000
13.000 1.1135 0.07255 0.06471 -0.0367 0.0450 1.0000
13.250 1.1220 0.07576 0.06815 -0.0368 0.0432 1.0000
13.500 1.1274 0.07915 0.07169 -0.0371 0.0416 1.0000
13.750 1.1339 0.08250 0.07506 -0.0374 0.0402 1.0000
14.000 1.1287 0.08732 0.08028 -0.0382 0.0394 1.0000
14.250 1.1197 0.09268 0.08601 -0.0397 0.0388 1.0000
14.500 1.1078 0.09865 0.09230 -0.0419 0.0383 1.0000
14.750 1.0930 0.10533 0.09927 -0.0449 0.0381 1.0000
15.000 1.0759 0.11282 0.10704 -0.0490 0.0381 1.0000
15.250 1.0564 0.12135 0.11580 -0.0541 0.0382 1.0000
15.500 1.0357 0.13094 0.12560 -0.0604 0.0386 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 403 AIRFOIL (e403-il)