EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 541 AIRFOIL (e541-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.75 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e541-il-1000000-n5.txt Download as CSV file: xf-e541-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4664 0.07054 0.06830 -0.1096 0.9008 0.0025
-14.000 -0.4973 0.06036 0.05784 -0.1163 0.8815 0.0024
-13.750 -0.5216 0.05429 0.05154 -0.1183 0.8666 0.0024
-13.500 -0.5586 0.04791 0.04486 -0.1183 0.8546 0.0024
-13.250 -0.5693 0.04498 0.04177 -0.1174 0.8451 0.0024
-13.000 -0.5925 0.04099 0.03752 -0.1153 0.8371 0.0024
-12.750 -0.6084 0.03788 0.03418 -0.1129 0.8296 0.0024
-12.500 -0.6190 0.03525 0.03132 -0.1103 0.8233 0.0024
-12.250 -0.6292 0.03260 0.02842 -0.1073 0.8171 0.0024
-12.000 -0.6337 0.03041 0.02598 -0.1046 0.8119 0.0024
-11.750 -0.6340 0.02843 0.02379 -0.1020 0.8069 0.0024
-11.500 -0.6282 0.02707 0.02224 -0.1000 0.8021 0.0023
-11.250 -0.6202 0.02575 0.02075 -0.0980 0.7978 0.0023
-11.000 -0.6127 0.02399 0.01876 -0.0959 0.7938 0.0023
-10.750 -0.6004 0.02280 0.01741 -0.0943 0.7897 0.0024
-10.500 -0.5862 0.02180 0.01626 -0.0929 0.7862 0.0023
-10.250 -0.5699 0.02105 0.01541 -0.0918 0.7832 0.0023
-10.000 -0.5539 0.01995 0.01416 -0.0904 0.7801 0.0024
-9.750 -0.5371 0.01909 0.01318 -0.0892 0.7771 0.0024
-9.500 -0.5192 0.01847 0.01249 -0.0882 0.7742 0.0024
-9.000 -0.4833 0.01720 0.01103 -0.0860 0.7690 0.0024
-8.750 -0.4656 0.01657 0.01033 -0.0848 0.7663 0.0024
-8.500 -0.4479 0.01598 0.00967 -0.0835 0.7634 0.0024
-8.250 -0.4295 0.01550 0.00912 -0.0824 0.7608 0.0024
-8.000 -0.4111 0.01504 0.00860 -0.0812 0.7584 0.0024
-7.750 -0.3931 0.01455 0.00805 -0.0800 0.7564 0.0025
-7.500 -0.3735 0.01417 0.00764 -0.0790 0.7543 0.0025
-7.250 -0.3545 0.01376 0.00719 -0.0779 0.7522 0.0025
-7.000 -0.3357 0.01336 0.00675 -0.0767 0.7500 0.0026
-6.750 -0.3167 0.01300 0.00634 -0.0756 0.7479 0.0027
-6.500 -0.2982 0.01264 0.00593 -0.0743 0.7457 0.0029
-6.250 -0.2793 0.01231 0.00557 -0.0730 0.7436 0.0034
-6.000 -0.2590 0.01205 0.00529 -0.0721 0.7418 0.0036
-5.750 -0.2390 0.01177 0.00500 -0.0711 0.7401 0.0041
-5.500 -0.2197 0.01148 0.00470 -0.0699 0.7382 0.0059
-5.250 -0.1997 0.01124 0.00445 -0.0688 0.7364 0.0071
-5.000 -0.1818 0.01094 0.00418 -0.0674 0.7346 0.0132
-4.750 -0.1645 0.01065 0.00393 -0.0658 0.7327 0.0225
-4.500 -0.1485 0.01039 0.00370 -0.0640 0.7308 0.0343
-4.250 -0.1368 0.01013 0.00351 -0.0612 0.7289 0.0541
-4.000 -0.1246 0.00978 0.00330 -0.0587 0.7272 0.0904
-3.750 -0.1135 0.00927 0.00307 -0.0560 0.7255 0.1561
-3.500 -0.1035 0.00867 0.00280 -0.0532 0.7237 0.2442
-3.250 -0.0994 0.00768 0.00239 -0.0496 0.7216 0.3943
-3.000 -0.0935 0.00641 0.00182 -0.0464 0.7196 0.5778
-2.750 -0.0731 0.00596 0.00182 -0.0453 0.7179 0.7054
-2.500 -0.0442 0.00603 0.00184 -0.0457 0.7165 0.7233
-2.000 0.0139 0.00633 0.00212 -0.0465 0.7137 0.7443
-1.750 0.0430 0.00649 0.00225 -0.0469 0.7121 0.7520
-1.500 0.0722 0.00655 0.00231 -0.0473 0.7106 0.7541
-1.250 0.1013 0.00654 0.00228 -0.0479 0.7090 0.7547
-1.000 0.1304 0.00653 0.00224 -0.0484 0.7073 0.7553
-0.750 0.1594 0.00653 0.00221 -0.0490 0.7056 0.7559
-0.500 0.1884 0.00654 0.00219 -0.0495 0.7038 0.7566
-0.250 0.2174 0.00655 0.00217 -0.0501 0.7019 0.7573
0.000 0.2463 0.00655 0.00215 -0.0506 0.6995 0.7579
0.250 0.2749 0.00653 0.00213 -0.0511 0.6962 0.7585
0.500 0.3035 0.00652 0.00211 -0.0515 0.6923 0.7591
0.750 0.3318 0.00652 0.00209 -0.0519 0.6885 0.7597
1.000 0.3603 0.00653 0.00208 -0.0523 0.6850 0.7603
1.250 0.3889 0.00652 0.00208 -0.0528 0.6813 0.7610
1.500 0.4173 0.00653 0.00209 -0.0532 0.6773 0.7617
1.750 0.4453 0.00655 0.00208 -0.0536 0.6733 0.7623
2.000 0.4738 0.00655 0.00209 -0.0540 0.6685 0.7628
2.250 0.5017 0.00656 0.00210 -0.0543 0.6628 0.7633
2.500 0.5294 0.00659 0.00212 -0.0546 0.6576 0.7638
2.750 0.5573 0.00660 0.00214 -0.0549 0.6506 0.7642
3.000 0.5843 0.00664 0.00217 -0.0550 0.6423 0.7646
3.250 0.6105 0.00668 0.00220 -0.0550 0.6313 0.7652
3.500 0.6361 0.00674 0.00224 -0.0548 0.6176 0.7657
3.750 0.6603 0.00684 0.00230 -0.0544 0.5978 0.7663
4.000 0.6811 0.00704 0.00241 -0.0533 0.5687 0.7669
4.250 0.6973 0.00739 0.00260 -0.0512 0.5278 0.7675
4.500 0.7115 0.00781 0.00285 -0.0488 0.4856 0.7683
4.750 0.7253 0.00823 0.00311 -0.0464 0.4472 0.7690
5.000 0.7372 0.00867 0.00338 -0.0436 0.4064 0.7698
5.250 0.7461 0.00907 0.00363 -0.0402 0.3707 0.7706
5.500 0.7570 0.00942 0.00389 -0.0372 0.3430 0.7714
5.750 0.7659 0.00991 0.00423 -0.0339 0.3083 0.7722
6.000 0.7767 0.01038 0.00458 -0.0311 0.2793 0.7730
6.250 0.7903 0.01078 0.00491 -0.0289 0.2582 0.7737
6.500 0.8011 0.01129 0.00531 -0.0263 0.2318 0.7745
6.750 0.8105 0.01188 0.00576 -0.0235 0.2024 0.7753
7.000 0.8205 0.01248 0.00625 -0.0209 0.1751 0.7761
7.250 0.8319 0.01307 0.00674 -0.0187 0.1520 0.7768
7.500 0.8434 0.01369 0.00726 -0.0165 0.1295 0.7774
7.750 0.8555 0.01431 0.00779 -0.0145 0.1109 0.7780
8.000 0.8694 0.01488 0.00830 -0.0129 0.0965 0.7787
8.250 0.8834 0.01545 0.00883 -0.0113 0.0833 0.7796
8.500 0.8975 0.01603 0.00938 -0.0097 0.0717 0.7804
8.750 0.9120 0.01662 0.00995 -0.0083 0.0614 0.7812
9.000 0.9263 0.01724 0.01055 -0.0069 0.0516 0.7819
9.250 0.9390 0.01795 0.01122 -0.0053 0.0406 0.7826
9.500 0.9539 0.01858 0.01184 -0.0040 0.0343 0.7833
9.750 0.9667 0.01933 0.01255 -0.0026 0.0262 0.7840
10.000 0.9801 0.02006 0.01326 -0.0013 0.0205 0.7847
10.250 0.9942 0.02078 0.01397 0.0000 0.0164 0.7855
10.500 1.0079 0.02153 0.01472 0.0012 0.0135 0.7862
10.750 1.0231 0.02220 0.01542 0.0022 0.0120 0.7869
11.000 1.0383 0.02289 0.01615 0.0031 0.0107 0.7877
11.250 1.0527 0.02363 0.01692 0.0041 0.0098 0.7884
11.500 1.0658 0.02447 0.01778 0.0052 0.0078 0.7891
11.750 1.0799 0.02526 0.01860 0.0062 0.0068 0.7898
12.000 1.0927 0.02615 0.01950 0.0072 0.0055 0.7905
12.250 1.1052 0.02708 0.02046 0.0082 0.0045 0.7912
12.500 1.1172 0.02806 0.02148 0.0092 0.0037 0.7918
12.750 1.1280 0.02915 0.02259 0.0103 0.0027 0.7924
13.000 1.1399 0.03017 0.02367 0.0112 0.0024 0.7933
13.250 1.1501 0.03132 0.02489 0.0123 0.0020 0.7943
13.500 1.1610 0.03246 0.02609 0.0132 0.0019 0.7951
13.750 1.1707 0.03372 0.02743 0.0141 0.0017 0.7960
14.000 1.1801 0.03503 0.02881 0.0150 0.0015 0.7968
14.250 1.1897 0.03635 0.03020 0.0158 0.0015 0.7975
14.500 1.1984 0.03778 0.03170 0.0166 0.0013 0.7983
14.750 1.2072 0.03923 0.03323 0.0173 0.0013 0.7991
15.000 1.2145 0.04086 0.03494 0.0180 0.0012 0.8000
15.250 1.2213 0.04257 0.03673 0.0186 0.0012 0.8007
15.500 1.2273 0.04438 0.03862 0.0192 0.0011 0.8016
15.750 1.2319 0.04639 0.04071 0.0197 0.0010 0.8024
16.000 1.2373 0.04838 0.04280 0.0201 0.0010 0.8031
16.250 1.2408 0.05063 0.04514 0.0204 0.0010 0.8039
16.500 1.2436 0.05299 0.04760 0.0206 0.0009 0.8046
16.750 1.2432 0.05580 0.05051 0.0207 0.0009 0.8053
17.000 1.2417 0.05883 0.05366 0.0207 0.0008 0.8059
17.250 1.2419 0.06178 0.05671 0.0204 0.0008 0.8066
17.500 1.2329 0.06600 0.06107 0.0199 0.0008 0.8072
17.750 1.2262 0.07006 0.06527 0.0191 0.0007 0.8080
18.000 1.2232 0.07379 0.06912 0.0181 0.0007 0.8087
18.250 1.2124 0.07882 0.07430 0.0166 0.0007 0.8094
18.500 1.2120 0.08244 0.07801 0.0153 0.0008 0.8102
18.750 1.2023 0.08759 0.08330 0.0132 0.0007 0.8108
19.000 1.1905 0.09329 0.08915 0.0108 0.0007 0.8114
19.250 1.1795 0.09906 0.09504 0.0081 0.0007 0.8120
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Polar data table (+)
Polar graphs
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