EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 543 AIRFOIL (e543-il) Reynolds number: 100,000 Max Cl/Cd: 35.29 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e543-il-100000-n5.txt Download as CSV file: xf-e543-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4379 0.10613 0.10099 -0.0587 1.0000 0.0179
-12.750 -0.4445 0.10000 0.09490 -0.0614 1.0000 0.0177
-12.500 -0.4602 0.09180 0.08670 -0.0658 1.0000 0.0175
-12.250 -0.4830 0.08413 0.07898 -0.0699 1.0000 0.0173
-12.000 -0.5052 0.07825 0.07303 -0.0722 1.0000 0.0170
-11.750 -0.5290 0.07316 0.06784 -0.0731 1.0000 0.0169
-11.500 -0.5525 0.06886 0.06343 -0.0728 1.0000 0.0167
-11.250 -0.5758 0.06512 0.05958 -0.0713 1.0000 0.0167
-11.000 -0.5985 0.06194 0.05627 -0.0688 1.0000 0.0165
-10.750 -0.6201 0.05943 0.05366 -0.0654 1.0000 0.0164
-10.500 -0.6444 0.05754 0.05170 -0.0608 1.0000 0.0165
-10.250 -0.6564 0.05426 0.04815 -0.0593 0.9929 0.0163
-10.000 -0.6559 0.05044 0.04394 -0.0596 0.9790 0.0163
-9.750 -0.6516 0.04702 0.04012 -0.0592 0.9654 0.0164
-9.500 -0.6394 0.04368 0.03633 -0.0592 0.9555 0.0165
-9.250 -0.6209 0.04059 0.03281 -0.0594 0.9463 0.0167
-9.000 -0.5907 0.03752 0.02928 -0.0611 0.9415 0.0170
-8.750 -0.5571 0.03484 0.02611 -0.0624 0.9351 0.0180
-8.500 -0.5229 0.03318 0.02438 -0.0647 0.9293 0.0193
-8.250 -0.4835 0.03143 0.02233 -0.0669 0.9246 0.0215
-8.000 -0.4489 0.02994 0.02079 -0.0685 0.9174 0.0231
-7.750 -0.4117 0.02851 0.01924 -0.0705 0.9121 0.0251
-7.500 -0.3838 0.02734 0.01802 -0.0711 0.9031 0.0276
-7.250 -0.3546 0.02625 0.01683 -0.0722 0.8955 0.0325
-7.000 -0.3330 0.02529 0.01579 -0.0717 0.8851 0.0378
-6.750 -0.3087 0.02430 0.01480 -0.0719 0.8772 0.0469
-6.500 -0.2902 0.02350 0.01404 -0.0708 0.8670 0.0637
-6.250 -0.2699 0.02256 0.01336 -0.0701 0.8589 0.1026
-6.000 -0.2562 0.02163 0.01291 -0.0683 0.8495 0.1825
-5.750 -0.2587 0.02039 0.01232 -0.0643 0.8394 0.2996
-5.500 -0.1995 0.02356 0.01702 -0.0628 0.8362 0.6101
-5.250 -0.1959 0.02346 0.01674 -0.0591 0.8277 0.6459
-5.000 -0.1944 0.02368 0.01681 -0.0545 0.8179 0.6694
-4.750 -0.1680 0.02454 0.01745 -0.0531 0.8122 0.6890
-4.500 -0.1460 0.02537 0.01812 -0.0511 0.8043 0.7050
-4.250 -0.1084 0.02659 0.01913 -0.0510 0.7991 0.7240
-4.000 -0.0542 0.02748 0.01978 -0.0542 0.7954 0.7351
-3.750 -0.0497 0.02744 0.01965 -0.0504 0.7874 0.7452
-3.500 -0.0113 0.02738 0.01938 -0.0522 0.7825 0.7482
-3.000 0.0143 0.02710 0.01888 -0.0476 0.7697 0.7611
-2.750 0.0489 0.02694 0.01856 -0.0490 0.7655 0.7634
-2.500 0.0739 0.02683 0.01835 -0.0488 0.7603 0.7668
-2.250 0.0639 0.02658 0.01805 -0.0428 0.7534 0.7757
-2.000 0.0966 0.02642 0.01775 -0.0439 0.7493 0.7773
-1.750 0.1234 0.02632 0.01757 -0.0440 0.7444 0.7795
-1.500 0.1443 0.02623 0.01743 -0.0431 0.7390 0.7825
-1.250 0.1598 0.02603 0.01714 -0.0414 0.7345 0.7866
-1.000 0.1642 0.02574 0.01678 -0.0379 0.7299 0.7920
-0.750 0.1861 0.02571 0.01673 -0.0372 0.7243 0.7938
-0.500 0.2107 0.02560 0.01657 -0.0369 0.7200 0.7959
-0.250 0.2351 0.02543 0.01632 -0.0367 0.7165 0.7980
0.000 0.2473 0.02535 0.01624 -0.0344 0.7114 0.8013
0.250 0.2474 0.02514 0.01601 -0.0303 0.7058 0.8061
0.500 0.2688 0.02497 0.01580 -0.0296 0.7020 0.8080
0.750 0.2980 0.02484 0.01560 -0.0301 0.6991 0.8093
1.000 0.3098 0.02492 0.01574 -0.0277 0.6929 0.8114
1.250 0.3288 0.02484 0.01565 -0.0266 0.6884 0.8132
1.500 0.3519 0.02471 0.01549 -0.0262 0.6850 0.8153
1.750 0.3670 0.02464 0.01544 -0.0245 0.6806 0.8179
2.000 0.3740 0.02460 0.01543 -0.0216 0.6747 0.8206
2.250 0.3927 0.02443 0.01525 -0.0206 0.6706 0.8229
2.500 0.4227 0.02431 0.01511 -0.0213 0.6676 0.8239
2.750 0.4331 0.02450 0.01539 -0.0186 0.6612 0.8257
3.000 0.4538 0.02447 0.01540 -0.0178 0.6562 0.8271
3.250 0.4821 0.02432 0.01525 -0.0183 0.6526 0.8282
3.500 0.4958 0.02441 0.01540 -0.0163 0.6466 0.8300
3.750 0.5133 0.02443 0.01549 -0.0150 0.6408 0.8319
4.000 0.5424 0.02425 0.01533 -0.0156 0.6368 0.8336
4.250 0.5554 0.02435 0.01549 -0.0137 0.6303 0.8359
4.500 0.5755 0.02433 0.01553 -0.0129 0.6242 0.8376
4.750 0.6086 0.02409 0.01532 -0.0141 0.6200 0.8385
5.000 0.6170 0.02433 0.01568 -0.0112 0.6120 0.8400
5.250 0.6440 0.02419 0.01562 -0.0113 0.6063 0.8411
5.500 0.6657 0.02417 0.01568 -0.0106 0.6000 0.8426
5.750 0.6825 0.02422 0.01583 -0.0090 0.5922 0.8445
6.000 0.7145 0.02396 0.01564 -0.0098 0.5864 0.8459
6.250 0.7229 0.02416 0.01597 -0.0070 0.5769 0.8482
6.500 0.7526 0.02392 0.01579 -0.0075 0.5698 0.8495
6.750 0.7648 0.02403 0.01602 -0.0054 0.5599 0.8515
7.000 0.7831 0.02401 0.01611 -0.0042 0.5503 0.8533
7.250 0.8087 0.02377 0.01595 -0.0039 0.5409 0.8545
7.500 0.8104 0.02398 0.01630 0.0001 0.5294 0.8565
7.750 0.8216 0.02406 0.01649 0.0027 0.5179 0.8588
8.000 0.8378 0.02408 0.01662 0.0043 0.5057 0.8611
8.250 0.8522 0.02420 0.01683 0.0061 0.4919 0.8635
8.500 0.8638 0.02448 0.01720 0.0081 0.4762 0.8660
8.750 0.8739 0.02489 0.01771 0.0100 0.4585 0.8683
9.000 0.8843 0.02528 0.01816 0.0120 0.4390 0.8704
9.250 0.8974 0.02557 0.01844 0.0138 0.4174 0.8725
9.500 0.9062 0.02617 0.01903 0.0158 0.3934 0.8749
9.750 0.9161 0.02680 0.01960 0.0176 0.3688 0.8774
10.000 0.9226 0.02773 0.02049 0.0194 0.3435 0.8803
10.250 0.9285 0.02881 0.02150 0.0211 0.3191 0.8835
10.500 0.9318 0.03001 0.02266 0.0231 0.2957 0.8865
10.750 0.9347 0.03132 0.02393 0.0249 0.2739 0.8898
11.000 0.9375 0.03277 0.02535 0.0264 0.2521 0.8932
11.250 0.9403 0.03434 0.02687 0.0277 0.2320 0.8966
11.500 0.9434 0.03598 0.02851 0.0288 0.2122 0.9000
11.750 0.9457 0.03764 0.03018 0.0300 0.1940 0.9035
12.000 0.9480 0.03942 0.03196 0.0309 0.1766 0.9075
12.250 0.9507 0.04130 0.03384 0.0317 0.1604 0.9119
12.500 0.9531 0.04324 0.03579 0.0323 0.1454 0.9165
12.750 0.9556 0.04524 0.03782 0.0329 0.1315 0.9220
13.000 0.9588 0.04733 0.03995 0.0331 0.1188 0.9288
13.250 0.9625 0.04954 0.04224 0.0331 0.1069 0.9370
13.500 0.9670 0.05191 0.04467 0.0325 0.0962 0.9480
13.750 0.9686 0.05436 0.04715 0.0319 0.0877 0.9742
14.000 0.9720 0.05679 0.04966 0.0315 0.0796 1.0000
14.250 0.9748 0.05951 0.05244 0.0309 0.0721 1.0000
14.500 0.9756 0.06253 0.05546 0.0301 0.0664 1.0000
14.750 0.9795 0.06527 0.05831 0.0294 0.0607 1.0000
15.000 0.9790 0.06855 0.06162 0.0285 0.0562 1.0000
15.250 0.9824 0.07145 0.06465 0.0277 0.0518 1.0000
15.500 0.9820 0.07487 0.06812 0.0266 0.0480 1.0000
15.750 0.9834 0.07811 0.07145 0.0256 0.0447 1.0000
16.000 0.9839 0.08157 0.07502 0.0244 0.0415 1.0000
16.250 0.9825 0.08523 0.07869 0.0230 0.0393 1.0000
16.500 0.9832 0.08883 0.08248 0.0217 0.0364 1.0000
16.750 0.9818 0.09275 0.08650 0.0200 0.0342 1.0000
17.000 0.9801 0.09667 0.09044 0.0184 0.0325 1.0000
17.250 0.9789 0.10074 0.09475 0.0167 0.0305 1.0000
17.500 0.9755 0.10519 0.09932 0.0145 0.0287 1.0000
17.750 0.9728 0.10950 0.10365 0.0123 0.0274 1.0000
18.000 0.9694 0.11412 0.10847 0.0101 0.0260 1.0000
18.250 0.9648 0.11907 0.11360 0.0075 0.0248 1.0000
18.500 0.9591 0.12428 0.11893 0.0046 0.0236 1.0000
18.750 0.9566 0.12881 0.12349 0.0019 0.0227 1.0000
19.000 0.9509 0.13416 0.12899 -0.0012 0.0220 1.0000
19.250 0.9407 0.14073 0.13579 -0.0050 0.0214 1.0000
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Polar data table (+)
Polar graphs
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