EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 541 AIRFOIL (e541-il) Reynolds number: 500,000 Max Cl/Cd: 79.76 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e541-il-500000-n5.txt Download as CSV file: xf-e541-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3646 0.10080 0.09831 -0.0859 0.9350 0.0044
-13.000 -0.4185 0.06726 0.06454 -0.1103 0.9173 0.0040
-12.750 -0.4473 0.05800 0.05495 -0.1166 0.8999 0.0039
-12.500 -0.4715 0.05251 0.04919 -0.1176 0.8840 0.0039
-12.000 -0.5191 0.04396 0.04008 -0.1140 0.8608 0.0038
-11.750 -0.5397 0.04025 0.03606 -0.1109 0.8522 0.0038
-11.500 -0.5500 0.03764 0.03319 -0.1080 0.8446 0.0037
-11.250 -0.5583 0.03503 0.03030 -0.1049 0.8382 0.0037
-11.000 -0.5669 0.03199 0.02689 -0.1013 0.8320 0.0037
-10.750 -0.5655 0.02976 0.02435 -0.0986 0.8271 0.0037
-10.500 -0.5584 0.02792 0.02225 -0.0965 0.8223 0.0036
-10.250 -0.5469 0.02642 0.02052 -0.0948 0.8178 0.0036
-9.750 -0.5146 0.02342 0.01704 -0.0923 0.8104 0.0037
-9.500 -0.4960 0.02242 0.01589 -0.0914 0.8069 0.0036
-9.250 -0.4766 0.02143 0.01474 -0.0905 0.8036 0.0037
-9.000 -0.4573 0.02064 0.01381 -0.0896 0.8007 0.0037
-8.750 -0.4383 0.01983 0.01289 -0.0886 0.7979 0.0038
-8.500 -0.4200 0.01905 0.01203 -0.0875 0.7949 0.0039
-8.250 -0.4016 0.01843 0.01132 -0.0864 0.7919 0.0039
-8.000 -0.3836 0.01784 0.01066 -0.0852 0.7890 0.0040
-7.750 -0.3661 0.01724 0.00997 -0.0839 0.7864 0.0042
-7.500 -0.3476 0.01676 0.00943 -0.0828 0.7838 0.0042
-7.250 -0.3294 0.01626 0.00886 -0.0816 0.7810 0.0044
-7.000 -0.3125 0.01569 0.00823 -0.0801 0.7784 0.0049
-6.750 -0.2935 0.01530 0.00780 -0.0790 0.7761 0.0052
-6.500 -0.2747 0.01491 0.00735 -0.0779 0.7739 0.0059
-6.250 -0.2553 0.01457 0.00695 -0.0767 0.7719 0.0071
-6.000 -0.2367 0.01420 0.00656 -0.0755 0.7697 0.0085
-5.750 -0.2181 0.01385 0.00622 -0.0743 0.7672 0.0118
-5.500 -0.2007 0.01347 0.00588 -0.0729 0.7648 0.0213
-5.250 -0.1833 0.01310 0.00557 -0.0714 0.7626 0.0350
-5.000 -0.1701 0.01260 0.00523 -0.0694 0.7605 0.0703
-4.750 -0.1608 0.01201 0.00487 -0.0666 0.7585 0.1241
-4.500 -0.1558 0.01144 0.00455 -0.0630 0.7565 0.1834
-4.250 -0.1572 0.01086 0.00426 -0.0580 0.7539 0.2536
-4.000 -0.1571 0.01010 0.00389 -0.0535 0.7512 0.3499
-3.750 -0.1599 0.00905 0.00335 -0.0486 0.7487 0.4822
-3.500 -0.1577 0.00818 0.00339 -0.0439 0.7466 0.6823
-3.250 -0.1297 0.00842 0.00361 -0.0439 0.7452 0.7171
-3.000 -0.1016 0.00863 0.00373 -0.0441 0.7438 0.7352
-2.750 -0.0727 0.00902 0.00410 -0.0442 0.7422 0.7464
-2.500 -0.0439 0.00947 0.00453 -0.0441 0.7403 0.7552
-2.250 -0.0164 0.00977 0.00477 -0.0441 0.7385 0.7645
-2.000 0.0125 0.00992 0.00491 -0.0443 0.7369 0.7661
-1.750 0.0408 0.00991 0.00485 -0.0447 0.7351 0.7668
-1.500 0.0691 0.00989 0.00479 -0.0451 0.7334 0.7676
-1.250 0.0976 0.00988 0.00473 -0.0455 0.7318 0.7684
-1.000 0.1262 0.00986 0.00466 -0.0460 0.7304 0.7692
-0.750 0.1549 0.00985 0.00460 -0.0465 0.7289 0.7700
-0.500 0.1824 0.00982 0.00457 -0.0468 0.7270 0.7710
-0.250 0.2101 0.00979 0.00453 -0.0472 0.7250 0.7719
0.000 0.2380 0.00975 0.00447 -0.0476 0.7228 0.7728
0.250 0.2661 0.00971 0.00441 -0.0480 0.7207 0.7737
0.500 0.2944 0.00967 0.00434 -0.0485 0.7185 0.7748
0.750 0.3230 0.00963 0.00427 -0.0490 0.7161 0.7759
1.000 0.3507 0.00958 0.00421 -0.0494 0.7130 0.7768
1.250 0.3778 0.00953 0.00415 -0.0496 0.7090 0.7777
1.500 0.4055 0.00947 0.00408 -0.0500 0.7051 0.7785
1.750 0.4339 0.00944 0.00403 -0.0504 0.7016 0.7789
2.000 0.4607 0.00942 0.00404 -0.0505 0.6977 0.7794
2.250 0.4875 0.00940 0.00406 -0.0506 0.6933 0.7800
2.500 0.5150 0.00939 0.00407 -0.0508 0.6890 0.7806
2.750 0.5419 0.00938 0.00408 -0.0509 0.6843 0.7811
3.000 0.5682 0.00937 0.00411 -0.0509 0.6786 0.7817
3.250 0.5954 0.00936 0.00410 -0.0510 0.6734 0.7822
3.500 0.6212 0.00935 0.00415 -0.0509 0.6666 0.7828
3.750 0.6473 0.00935 0.00415 -0.0508 0.6593 0.7834
4.000 0.6724 0.00935 0.00420 -0.0506 0.6499 0.7841
4.250 0.6973 0.00936 0.00424 -0.0503 0.6394 0.7847
4.500 0.7213 0.00938 0.00427 -0.0498 0.6261 0.7855
4.750 0.7436 0.00943 0.00430 -0.0490 0.6072 0.7862
5.000 0.7625 0.00956 0.00435 -0.0474 0.5794 0.7870
5.250 0.7749 0.00985 0.00449 -0.0446 0.5404 0.7882
5.500 0.7810 0.01030 0.00472 -0.0406 0.4962 0.7894
5.750 0.7839 0.01072 0.00498 -0.0361 0.4596 0.7906
6.000 0.7866 0.01123 0.00532 -0.0316 0.4220 0.7916
6.250 0.7911 0.01184 0.00577 -0.0277 0.3863 0.7926
6.500 0.7973 0.01244 0.00624 -0.0243 0.3540 0.7934
6.750 0.8046 0.01305 0.00675 -0.0212 0.3242 0.7941
7.000 0.8118 0.01372 0.00731 -0.0181 0.2938 0.7949
7.250 0.8192 0.01443 0.00792 -0.0153 0.2634 0.7957
7.500 0.8254 0.01526 0.00859 -0.0124 0.2289 0.7966
7.750 0.8351 0.01599 0.00922 -0.0102 0.2028 0.7974
8.000 0.8439 0.01680 0.00991 -0.0079 0.1739 0.7983
8.250 0.8541 0.01759 0.01059 -0.0059 0.1496 0.7994
8.500 0.8658 0.01834 0.01126 -0.0042 0.1283 0.8004
8.750 0.8774 0.01912 0.01197 -0.0026 0.1101 0.8013
9.000 0.8903 0.01986 0.01267 -0.0011 0.0947 0.8022
9.250 0.9034 0.02061 0.01338 0.0003 0.0810 0.8031
9.500 0.9165 0.02138 0.01412 0.0016 0.0694 0.8039
9.750 0.9294 0.02218 0.01488 0.0029 0.0586 0.8047
10.000 0.9422 0.02301 0.01568 0.0041 0.0486 0.8055
10.250 0.9558 0.02381 0.01648 0.0052 0.0409 0.8063
10.500 0.9680 0.02470 0.01736 0.0065 0.0333 0.8070
10.750 0.9795 0.02563 0.01828 0.0078 0.0267 0.8077
11.000 0.9920 0.02652 0.01919 0.0089 0.0220 0.8084
11.250 1.0038 0.02748 0.02018 0.0100 0.0185 0.8092
11.500 1.0172 0.02835 0.02111 0.0109 0.0166 0.8099
11.750 1.0293 0.02933 0.02213 0.0120 0.0145 0.8107
12.000 1.0400 0.03044 0.02327 0.0130 0.0124 0.8115
12.250 1.0530 0.03140 0.02431 0.0139 0.0112 0.8125
12.500 1.0645 0.03248 0.02546 0.0148 0.0099 0.8135
12.750 1.0744 0.03371 0.02670 0.0157 0.0077 0.8145
13.000 1.0853 0.03490 0.02796 0.0165 0.0066 0.8155
13.250 1.0947 0.03624 0.02934 0.0173 0.0054 0.8165
13.500 1.1036 0.03765 0.03082 0.0182 0.0049 0.8174
13.750 1.1124 0.03911 0.03239 0.0189 0.0043 0.8182
14.000 1.1203 0.04069 0.03403 0.0196 0.0037 0.8191
14.250 1.1273 0.04239 0.03580 0.0203 0.0034 0.8199
14.500 1.1316 0.04438 0.03788 0.0210 0.0030 0.8207
14.750 1.1379 0.04619 0.03981 0.0216 0.0029 0.8215
15.000 1.1425 0.04824 0.04198 0.0221 0.0027 0.8224
15.250 1.1464 0.05041 0.04427 0.0225 0.0026 0.8232
15.500 1.1506 0.05262 0.04659 0.0227 0.0024 0.8240
15.750 1.1526 0.05513 0.04923 0.0229 0.0022 0.8249
16.000 1.1543 0.05776 0.05198 0.0229 0.0022 0.8258
16.250 1.1547 0.06064 0.05498 0.0228 0.0021 0.8267
16.500 1.1543 0.06372 0.05818 0.0225 0.0020 0.8276
16.750 1.1528 0.06703 0.06163 0.0219 0.0019 0.8285
17.000 1.1480 0.07091 0.06565 0.0211 0.0019 0.8294
17.250 1.1444 0.07477 0.06965 0.0201 0.0018 0.8303
17.500 1.1331 0.07993 0.07496 0.0185 0.0017 0.8311
17.750 1.1241 0.08495 0.08013 0.0167 0.0017 0.8319
18.000 1.1179 0.08970 0.08501 0.0147 0.0017 0.8327
18.250 1.1032 0.09603 0.09151 0.0120 0.0017 0.8334
18.500 1.0993 0.10072 0.09633 0.0097 0.0017 0.8342
19.000 1.0753 0.11330 0.10921 0.0033 0.0017 0.8356
19.250 1.0589 0.12067 0.11673 -0.0006 0.0016 0.8362
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