EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 543 AIRFOIL (e543-il) Reynolds number: 200,000 Max Cl/Cd: 58.57 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e543-il-200000-n5.txt Download as CSV file: xf-e543-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 543 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4776 0.08862 0.08501 -0.0646 1.0000 0.0103
-12.500 -0.5300 0.07420 0.07037 -0.0725 1.0000 0.0099
-11.750 -0.6532 0.05342 0.04856 -0.0708 1.0000 0.0092
-11.500 -0.6690 0.05071 0.04570 -0.0681 1.0000 0.0092
-11.250 -0.6856 0.04824 0.04307 -0.0647 1.0000 0.0092
-11.000 -0.6869 0.04472 0.03925 -0.0646 0.9926 0.0091
-10.750 -0.6825 0.04156 0.03578 -0.0646 0.9770 0.0091
-10.500 -0.6736 0.03844 0.03225 -0.0647 0.9627 0.0092
-10.250 -0.6548 0.03558 0.02905 -0.0657 0.9523 0.0092
-10.000 -0.6278 0.03316 0.02635 -0.0677 0.9443 0.0093
-9.750 -0.5975 0.03107 0.02403 -0.0697 0.9355 0.0095
-9.500 -0.5628 0.02928 0.02202 -0.0723 0.9276 0.0098
-9.250 -0.5273 0.02765 0.02020 -0.0745 0.9184 0.0100
-9.000 -0.4897 0.02621 0.01857 -0.0771 0.9095 0.0103
-8.750 -0.4557 0.02492 0.01711 -0.0790 0.8982 0.0110
-8.500 -0.4250 0.02385 0.01588 -0.0804 0.8859 0.0114
-8.250 -0.3988 0.02283 0.01475 -0.0811 0.8736 0.0121
-7.750 -0.3559 0.02132 0.01303 -0.0807 0.8498 0.0140
-7.500 -0.3378 0.02066 0.01227 -0.0797 0.8387 0.0151
-7.250 -0.3187 0.02010 0.01163 -0.0788 0.8288 0.0182
-7.000 -0.3033 0.01952 0.01098 -0.0772 0.8184 0.0210
-6.750 -0.2875 0.01893 0.01033 -0.0757 0.8096 0.0243
-6.500 -0.2730 0.01835 0.00974 -0.0739 0.8008 0.0322
-6.250 -0.2598 0.01775 0.00917 -0.0719 0.7931 0.0462
-6.000 -0.2486 0.01712 0.00864 -0.0697 0.7849 0.0693
-5.750 -0.2396 0.01645 0.00811 -0.0670 0.7776 0.1059
-5.500 -0.2354 0.01575 0.00763 -0.0636 0.7695 0.1530
-5.250 -0.2381 0.01504 0.00716 -0.0589 0.7629 0.2144
-5.000 -0.2449 0.01412 0.00666 -0.0535 0.7554 0.3052
-4.750 -0.2551 0.01294 0.00608 -0.0475 0.7493 0.4352
-4.500 -0.2328 0.01384 0.00802 -0.0440 0.7442 0.6409
-4.250 -0.2152 0.01391 0.00797 -0.0422 0.7381 0.6713
-4.000 -0.1922 0.01421 0.00810 -0.0411 0.7331 0.6900
-3.750 -0.1657 0.01484 0.00861 -0.0403 0.7280 0.7048
-3.500 -0.1352 0.01583 0.00953 -0.0395 0.7230 0.7183
-3.250 -0.1031 0.01692 0.01053 -0.0389 0.7187 0.7311
-3.000 -0.0688 0.01759 0.01108 -0.0392 0.7149 0.7363
-2.750 -0.0566 0.01706 0.01045 -0.0374 0.7093 0.7439
-2.500 -0.0293 0.01707 0.01036 -0.0373 0.7046 0.7451
-2.250 -0.0020 0.01706 0.01023 -0.0373 0.7007 0.7465
-2.000 0.0243 0.01703 0.01012 -0.0372 0.6968 0.7481
-1.750 0.0491 0.01696 0.01000 -0.0369 0.6922 0.7500
-1.500 0.0735 0.01684 0.00979 -0.0366 0.6879 0.7522
-1.250 0.0976 0.01664 0.00949 -0.0364 0.6843 0.7550
-1.000 0.1177 0.01624 0.00899 -0.0360 0.6802 0.7593
-0.750 0.1432 0.01618 0.00889 -0.0358 0.6760 0.7604
-0.500 0.1694 0.01614 0.00881 -0.0358 0.6721 0.7614
-0.250 0.1963 0.01608 0.00868 -0.0359 0.6686 0.7624
0.000 0.2224 0.01602 0.00858 -0.0359 0.6650 0.7634
0.250 0.2474 0.01598 0.00854 -0.0357 0.6609 0.7648
0.500 0.2731 0.01593 0.00846 -0.0356 0.6569 0.7662
0.750 0.2996 0.01585 0.00834 -0.0357 0.6535 0.7676
1.000 0.3265 0.01578 0.00822 -0.0360 0.6503 0.7689
1.250 0.3510 0.01570 0.00816 -0.0359 0.6460 0.7705
1.500 0.3766 0.01562 0.00807 -0.0360 0.6418 0.7725
1.750 0.4034 0.01552 0.00793 -0.0364 0.6382 0.7743
2.000 0.4317 0.01545 0.00779 -0.0370 0.6350 0.7756
2.250 0.4558 0.01545 0.00785 -0.0366 0.6303 0.7763
2.500 0.4814 0.01544 0.00788 -0.0365 0.6257 0.7771
2.750 0.5083 0.01543 0.00786 -0.0366 0.6215 0.7779
3.000 0.5345 0.01544 0.00789 -0.0366 0.6171 0.7788
3.250 0.5587 0.01545 0.00797 -0.0362 0.6115 0.7800
3.500 0.5848 0.01545 0.00799 -0.0361 0.6066 0.7812
3.750 0.6117 0.01546 0.00799 -0.0363 0.6020 0.7822
4.000 0.6354 0.01547 0.00809 -0.0359 0.5958 0.7834
4.250 0.6614 0.01545 0.00810 -0.0359 0.5903 0.7845
4.500 0.6871 0.01546 0.00814 -0.0359 0.5846 0.7857
4.750 0.7110 0.01547 0.00822 -0.0355 0.5777 0.7870
5.000 0.7381 0.01546 0.00820 -0.0357 0.5718 0.7882
5.250 0.7607 0.01548 0.00832 -0.0352 0.5637 0.7896
5.500 0.7866 0.01548 0.00833 -0.0352 0.5564 0.7911
5.750 0.8078 0.01552 0.00848 -0.0342 0.5472 0.7921
6.000 0.8310 0.01555 0.00855 -0.0335 0.5386 0.7931
6.250 0.8519 0.01560 0.00870 -0.0325 0.5281 0.7941
6.500 0.8726 0.01567 0.00884 -0.0314 0.5173 0.7952
6.750 0.8929 0.01574 0.00897 -0.0303 0.5054 0.7963
7.000 0.9117 0.01583 0.00911 -0.0289 0.4912 0.7975
7.250 0.9288 0.01595 0.00927 -0.0272 0.4744 0.7989
7.500 0.9436 0.01611 0.00944 -0.0251 0.4540 0.8003
7.750 0.9537 0.01632 0.00960 -0.0221 0.4314 0.8019
8.000 0.9619 0.01665 0.00987 -0.0190 0.4062 0.8036
8.250 0.9683 0.01716 0.01028 -0.0157 0.3796 0.8056
8.500 0.9725 0.01782 0.01083 -0.0123 0.3535 0.8075
8.750 0.9757 0.01854 0.01150 -0.0088 0.3278 0.8090
9.000 0.9787 0.01936 0.01225 -0.0056 0.3048 0.8105
9.250 0.9814 0.02028 0.01311 -0.0025 0.2813 0.8122
9.500 0.9840 0.02129 0.01408 0.0003 0.2600 0.8139
9.750 0.9871 0.02237 0.01511 0.0028 0.2381 0.8157
10.000 0.9896 0.02358 0.01626 0.0052 0.2176 0.8176
10.250 0.9931 0.02484 0.01747 0.0072 0.1987 0.8195
10.500 0.9971 0.02615 0.01874 0.0090 0.1798 0.8213
10.750 1.0012 0.02752 0.02009 0.0106 0.1628 0.8230
11.000 1.0044 0.02893 0.02148 0.0124 0.1467 0.8247
11.250 1.0081 0.03039 0.02293 0.0139 0.1321 0.8266
11.500 1.0124 0.03187 0.02441 0.0153 0.1187 0.8287
11.750 1.0170 0.03340 0.02595 0.0165 0.1065 0.8308
12.000 1.0219 0.03498 0.02754 0.0175 0.0955 0.8329
12.250 1.0267 0.03665 0.02921 0.0184 0.0856 0.8350
12.500 1.0309 0.03842 0.03098 0.0192 0.0765 0.8370
12.750 1.0365 0.04010 0.03273 0.0200 0.0687 0.8390
13.000 1.0410 0.04190 0.03457 0.0207 0.0615 0.8408
13.250 1.0440 0.04389 0.03660 0.0213 0.0555 0.8429
13.500 1.0494 0.04576 0.03855 0.0218 0.0499 0.8451
13.750 1.0529 0.04788 0.04072 0.0221 0.0451 0.8475
14.000 1.0569 0.05005 0.04295 0.0223 0.0407 0.8500
14.250 1.0605 0.05232 0.04531 0.0223 0.0369 0.8525
14.500 1.0632 0.05474 0.04778 0.0223 0.0335 0.8548
14.750 1.0663 0.05714 0.05029 0.0223 0.0307 0.8574
15.000 1.0684 0.05972 0.05296 0.0221 0.0281 0.8603
15.250 1.0701 0.06243 0.05577 0.0218 0.0261 0.8637
15.500 1.0718 0.06524 0.05869 0.0214 0.0239 0.8671
15.750 1.0713 0.06837 0.06189 0.0207 0.0222 0.8705
16.000 1.0724 0.07133 0.06503 0.0202 0.0206 0.8743
16.250 1.0720 0.07458 0.06840 0.0194 0.0192 0.8785
16.500 1.0699 0.07818 0.07210 0.0183 0.0179 0.8829
16.750 1.0689 0.08167 0.07576 0.0173 0.0166 0.8877
17.000 1.0668 0.08539 0.07961 0.0161 0.0155 0.8938
17.500 1.0596 0.09349 0.08803 0.0132 0.0136 0.9106
17.750 1.0559 0.09785 0.09255 0.0112 0.0127 0.9259
18.000 1.0498 0.10243 0.09729 0.0087 0.0122 0.9943
18.250 1.0423 0.10728 0.10223 0.0067 0.0120 1.0000
18.500 1.0388 0.11194 0.10706 0.0043 0.0108 1.0000
18.750 1.0330 0.11706 0.11230 0.0016 0.0103 1.0000
19.000 1.0273 0.12225 0.11760 -0.0013 0.0099 1.0000
19.250 1.0195 0.12790 0.12336 -0.0045 0.0096 1.0000
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