EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 541 AIRFOIL (e541-il) Reynolds number: 50,000 Max Cl/Cd: 20.99 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e541-il-50000-n5.txt Download as CSV file: xf-e541-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 541 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4482 0.10373 0.09707 -0.0695 1.0000 0.0328
-11.750 -0.4654 0.10022 0.09364 -0.0689 1.0000 0.0326
-11.500 -0.4838 0.09749 0.09098 -0.0675 1.0000 0.0324
-11.250 -0.5061 0.09473 0.08826 -0.0658 1.0000 0.0321
-11.000 -0.5324 0.09185 0.08541 -0.0639 1.0000 0.0320
-10.750 -0.5578 0.08928 0.08284 -0.0615 1.0000 0.0318
-10.500 -0.5759 0.08545 0.07893 -0.0616 0.9968 0.0316
-10.250 -0.5881 0.08117 0.07450 -0.0629 0.9909 0.0313
-10.000 -0.6038 0.07714 0.07033 -0.0630 0.9844 0.0312
-9.750 -0.6191 0.07385 0.06677 -0.0619 0.9779 0.0311
-9.500 -0.6319 0.07106 0.06376 -0.0601 0.9715 0.0309
-9.250 -0.6452 0.06844 0.06091 -0.0572 0.9650 0.0309
-9.000 -0.6519 0.06551 0.05769 -0.0549 0.9589 0.0308
-8.750 -0.6548 0.06247 0.05431 -0.0527 0.9537 0.0308
-8.500 -0.6596 0.05986 0.05137 -0.0493 0.9479 0.0308
-8.250 -0.6554 0.05699 0.04809 -0.0472 0.9436 0.0310
-8.000 -0.6488 0.05445 0.04510 -0.0450 0.9396 0.0316
-7.750 -0.6447 0.05238 0.04254 -0.0417 0.9345 0.0326
-7.500 -0.6297 0.04979 0.03968 -0.0406 0.9312 0.0338
-7.250 -0.6090 0.04770 0.03739 -0.0405 0.9287 0.0361
-7.000 -0.5808 0.04562 0.03500 -0.0408 0.9267 0.0382
-6.750 -0.5528 0.04385 0.03292 -0.0404 0.9241 0.0399
-6.500 -0.4879 0.04165 0.03035 -0.0453 0.9248 0.0464
-6.250 -0.4076 0.03989 0.02845 -0.0524 0.9268 0.0606
-6.000 -0.3933 0.03927 0.02777 -0.0501 0.9225 0.0717
-5.750 -0.3785 0.03837 0.02695 -0.0482 0.9190 0.0890
-5.500 -0.3674 0.03724 0.02607 -0.0460 0.9158 0.1247
-5.250 -0.3157 0.03850 0.03062 -0.0427 0.9163 0.6356
-5.000 -0.3277 0.03897 0.03092 -0.0363 0.9113 0.6889
-4.750 -0.3461 0.03959 0.03143 -0.0282 0.9049 0.7206
-4.500 -0.3134 0.04243 0.03384 -0.0255 0.9026 0.7734
-4.250 -0.2106 0.04520 0.03591 -0.0340 0.9045 0.8273
-4.000 -0.1709 0.04533 0.03570 -0.0362 0.9025 0.8449
-3.750 -0.1370 0.04511 0.03514 -0.0382 0.9003 0.8543
-3.500 -0.1230 0.04508 0.03491 -0.0366 0.8966 0.8640
-3.250 -0.1005 0.04492 0.03455 -0.0366 0.8928 0.8710
-3.000 -0.0833 0.04484 0.03429 -0.0357 0.8893 0.8785
-2.750 -0.0519 0.04459 0.03383 -0.0375 0.8867 0.8839
-2.500 -0.0392 0.04461 0.03368 -0.0358 0.8831 0.8908
-2.250 -0.0213 0.04452 0.03346 -0.0351 0.8788 0.8956
-2.000 -0.0048 0.04451 0.03332 -0.0341 0.8749 0.9010
-1.750 0.0196 0.04441 0.03309 -0.0347 0.8720 0.9052
-1.500 0.0391 0.04438 0.03293 -0.0343 0.8681 0.9091
-1.250 0.0479 0.04449 0.03296 -0.0319 0.8630 0.9136
-1.000 0.0631 0.04456 0.03294 -0.0307 0.8591 0.9177
-0.750 0.0966 0.04445 0.03273 -0.0329 0.8566 0.9200
-0.500 0.1014 0.04461 0.03285 -0.0299 0.8503 0.9236
-0.250 0.1199 0.04469 0.03286 -0.0293 0.8460 0.9267
0.000 0.1444 0.04473 0.03284 -0.0297 0.8427 0.9293
0.250 0.1430 0.04500 0.03310 -0.0256 0.8358 0.9327
0.500 0.1673 0.04505 0.03310 -0.0260 0.8314 0.9346
0.750 0.1983 0.04507 0.03309 -0.0276 0.8281 0.9363
1.000 0.1981 0.04536 0.03338 -0.0238 0.8203 0.9392
1.250 0.2214 0.04545 0.03346 -0.0239 0.8157 0.9412
1.500 0.2261 0.04572 0.03373 -0.0208 0.8088 0.9436
1.750 0.2411 0.04587 0.03389 -0.0194 0.8029 0.9456
2.000 0.2653 0.04599 0.03403 -0.0197 0.7978 0.9469
2.250 0.2764 0.04621 0.03427 -0.0178 0.7900 0.9486
2.500 0.3082 0.04625 0.03436 -0.0193 0.7858 0.9498
2.750 0.3104 0.04657 0.03472 -0.0159 0.7763 0.9520
3.000 0.3405 0.04658 0.03478 -0.0169 0.7717 0.9530
3.250 0.3402 0.04690 0.03514 -0.0130 0.7616 0.9550
3.500 0.3605 0.04700 0.03529 -0.0124 0.7552 0.9567
3.750 0.3724 0.04717 0.03556 -0.0104 0.7463 0.9583
4.000 0.3865 0.04737 0.03583 -0.0090 0.7374 0.9594
4.250 0.4138 0.04734 0.03589 -0.0095 0.7307 0.9603
4.500 0.4239 0.04761 0.03625 -0.0074 0.7202 0.9621
4.750 0.4492 0.04757 0.03635 -0.0075 0.7127 0.9634
5.000 0.4664 0.04763 0.03652 -0.0063 0.7031 0.9650
5.250 0.4748 0.04782 0.03681 -0.0039 0.6919 0.9666
5.500 0.4894 0.04784 0.03694 -0.0021 0.6819 0.9680
5.750 0.5154 0.04752 0.03677 -0.0018 0.6739 0.9692
6.000 0.5297 0.04763 0.03705 -0.0004 0.6615 0.9709
6.250 0.5468 0.04768 0.03725 0.0006 0.6491 0.9725
6.500 0.5646 0.04762 0.03737 0.0017 0.6366 0.9742
6.750 0.5821 0.04749 0.03740 0.0029 0.6239 0.9758
7.000 0.5997 0.04730 0.03742 0.0043 0.6112 0.9774
7.250 0.6178 0.04699 0.03729 0.0057 0.5979 0.9790
7.500 0.6365 0.04663 0.03711 0.0071 0.5843 0.9809
7.750 0.6572 0.04617 0.03688 0.0082 0.5697 0.9828
8.000 0.6809 0.04557 0.03651 0.0089 0.5543 0.9847
8.250 0.7052 0.04476 0.03598 0.0099 0.5383 0.9868
8.500 0.7316 0.04372 0.03517 0.0109 0.5215 0.9889
8.750 0.7558 0.04278 0.03445 0.0122 0.5018 0.9910
9.000 0.7807 0.04176 0.03361 0.0136 0.4780 0.9932
9.250 0.8075 0.04071 0.03267 0.0149 0.4487 0.9954
9.500 0.8284 0.04024 0.03222 0.0165 0.4134 0.9980
9.750 0.8424 0.04014 0.03208 0.0188 0.3767 1.0000
10.000 0.8418 0.04054 0.03236 0.0228 0.3470 1.0000
10.250 0.8372 0.04119 0.03291 0.0269 0.3192 1.0000
10.500 0.8302 0.04200 0.03364 0.0311 0.2928 1.0000
10.750 0.8228 0.04290 0.03445 0.0351 0.2683 1.0000
11.000 0.8157 0.04386 0.03531 0.0389 0.2459 1.0000
11.250 0.8093 0.04505 0.03641 0.0421 0.2231 1.0000
11.500 0.8056 0.04647 0.03775 0.0446 0.2007 1.0000
11.750 0.8039 0.04812 0.03931 0.0465 0.1796 1.0000
12.000 0.8038 0.05000 0.04113 0.0479 0.1589 1.0000
12.250 0.8051 0.05200 0.04309 0.0489 0.1407 1.0000
12.500 0.8067 0.05417 0.04519 0.0496 0.1247 1.0000
12.750 0.8103 0.05636 0.04737 0.0502 0.1108 1.0000
13.000 0.8148 0.05863 0.04968 0.0505 0.0984 1.0000
13.250 0.8205 0.06096 0.05216 0.0507 0.0877 1.0000
13.500 0.8307 0.06311 0.05442 0.0510 0.0792 1.0000
13.750 0.8380 0.06542 0.05674 0.0510 0.0721 1.0000
14.000 0.8449 0.06811 0.05970 0.0509 0.0653 1.0000
14.250 0.8537 0.07050 0.06214 0.0508 0.0602 1.0000
14.500 0.8639 0.07342 0.06536 0.0508 0.0561 1.0000
14.750 0.8638 0.07712 0.06936 0.0503 0.0526 1.0000
15.000 0.8627 0.08056 0.07294 0.0494 0.0495 1.0000
15.250 0.8641 0.08404 0.07644 0.0485 0.0467 1.0000
15.500 0.8540 0.08928 0.08206 0.0469 0.0457 1.0000
15.750 0.8403 0.09529 0.08839 0.0446 0.0450 1.0000
16.000 0.8230 0.10206 0.09543 0.0414 0.0447 1.0000
16.250 0.8034 0.10972 0.10332 0.0374 0.0447 1.0000
16.500 0.7819 0.11838 0.11217 0.0324 0.0449 1.0000
16.750 0.7593 0.12810 0.12202 0.0266 0.0454 1.0000
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