EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 554 AIRFOIL (e554-il) Reynolds number: 100,000 Max Cl/Cd: 36.38 at α=12.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e554-il-100000.txt Download as CSV file: xf-e554-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 554 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5490 0.08857 0.08326 -0.0649 1.0000 0.0504
-12.750 -0.5671 0.08263 0.07726 -0.0676 1.0000 0.0499
-12.500 -0.5882 0.07690 0.07144 -0.0703 1.0000 0.0493
-12.250 -0.6096 0.07168 0.06612 -0.0725 1.0000 0.0485
-12.000 -0.6353 0.06666 0.06094 -0.0743 1.0000 0.0479
-11.750 -0.6589 0.06226 0.05638 -0.0753 1.0000 0.0473
-11.500 -0.6810 0.05854 0.05248 -0.0752 1.0000 0.0468
-11.250 -0.7046 0.05535 0.04910 -0.0741 1.0000 0.0462
-11.000 -0.7263 0.05298 0.04658 -0.0715 1.0000 0.0459
-10.750 -0.7374 0.05081 0.04430 -0.0690 1.0000 0.0464
-10.500 -0.7457 0.04850 0.04182 -0.0665 1.0000 0.0465
-10.250 -0.7502 0.04657 0.03976 -0.0640 1.0000 0.0472
-10.000 -0.7552 0.04481 0.03784 -0.0611 1.0000 0.0481
-9.750 -0.7602 0.04313 0.03600 -0.0578 1.0000 0.0487
-9.500 -0.7665 0.04175 0.03445 -0.0543 1.0000 0.0493
-9.250 -0.7719 0.04051 0.03304 -0.0508 1.0000 0.0498
-9.000 -0.7620 0.03884 0.03106 -0.0498 0.9976 0.0507
-8.750 -0.7169 0.03617 0.02846 -0.0531 0.9910 0.0533
-8.500 -0.6699 0.03420 0.02626 -0.0570 0.9824 0.0585
-8.250 -0.6272 0.03229 0.02452 -0.0600 0.9726 0.0662
-8.000 -0.5862 0.03052 0.02287 -0.0626 0.9616 0.0767
-7.750 -0.5505 0.02858 0.02127 -0.0652 0.9494 0.0943
-7.500 -0.5180 0.02630 0.01927 -0.0685 0.9362 0.1248
-7.250 -0.4975 0.02178 0.01575 -0.0736 0.9213 0.2309
-7.000 -0.4465 0.02310 0.01782 -0.0768 0.9120 0.4198
-6.750 -0.4010 0.02525 0.01983 -0.0771 0.8989 0.4491
-6.500 -0.3501 0.02806 0.02260 -0.0765 0.8881 0.4680
-6.250 -0.2956 0.03066 0.02508 -0.0763 0.8781 0.4839
-6.000 -0.2567 0.03177 0.02600 -0.0761 0.8631 0.4989
-5.750 -0.2012 0.03493 0.02907 -0.0733 0.8501 0.5053
-5.500 -0.1689 0.03517 0.02911 -0.0732 0.8348 0.5187
-5.250 -0.1475 0.03456 0.02828 -0.0737 0.8194 0.5335
-5.000 -0.0983 0.03628 0.02985 -0.0715 0.8069 0.5384
-4.750 -0.0937 0.03473 0.02812 -0.0718 0.7921 0.5515
-4.500 -0.0586 0.03547 0.02876 -0.0697 0.7798 0.5557
-4.250 -0.0358 0.03496 0.02806 -0.0696 0.7689 0.5634
-4.000 -0.0247 0.03382 0.02679 -0.0694 0.7568 0.5712
-3.750 0.0007 0.03379 0.02665 -0.0681 0.7463 0.5756
-3.500 0.0178 0.03277 0.02545 -0.0687 0.7371 0.5826
-3.250 0.0335 0.03173 0.02430 -0.0692 0.7275 0.5883
-3.000 0.0591 0.03158 0.02405 -0.0684 0.7195 0.5918
-2.750 0.0794 0.03112 0.02351 -0.0681 0.7109 0.5965
-2.500 0.1007 0.02996 0.02215 -0.0702 0.7029 0.6027
-2.250 0.1239 0.02955 0.02165 -0.0701 0.6957 0.6064
-2.000 0.1463 0.02936 0.02142 -0.0695 0.6880 0.6094
-1.750 0.1735 0.02899 0.02090 -0.0701 0.6825 0.6133
-1.500 0.1952 0.02856 0.02042 -0.0709 0.6751 0.6186
-1.250 0.2220 0.02800 0.01973 -0.0724 0.6686 0.6229
-1.000 0.2497 0.02784 0.01947 -0.0724 0.6637 0.6256
-0.750 0.2690 0.02788 0.01957 -0.0716 0.6564 0.6294
-0.500 0.2959 0.02769 0.01930 -0.0724 0.6510 0.6342
-0.250 0.3294 0.02727 0.01867 -0.0751 0.6467 0.6394
0.000 0.3477 0.02745 0.01895 -0.0739 0.6402 0.6420
0.250 0.3717 0.02750 0.01901 -0.0735 0.6347 0.6456
0.500 0.4009 0.02743 0.01885 -0.0742 0.6304 0.6504
0.750 0.4272 0.02755 0.01893 -0.0754 0.6256 0.6558
1.000 0.4485 0.02777 0.01922 -0.0751 0.6199 0.6592
1.250 0.4745 0.02784 0.01928 -0.0750 0.6154 0.6628
1.500 0.5051 0.02784 0.01920 -0.0757 0.6118 0.6677
1.750 0.5247 0.02842 0.01985 -0.0760 0.6060 0.6735
2.000 0.5458 0.02878 0.02029 -0.0754 0.6010 0.6776
2.250 0.5734 0.02887 0.02038 -0.0755 0.5970 0.6822
2.500 0.6060 0.02891 0.02034 -0.0766 0.5938 0.6877
2.750 0.6173 0.03000 0.02160 -0.0758 0.5874 0.6928
3.000 0.6375 0.03047 0.02216 -0.0749 0.5826 0.6974
3.250 0.6680 0.03053 0.02220 -0.0755 0.5790 0.7038
3.500 0.6991 0.03075 0.02239 -0.0765 0.5757 0.7103
3.750 0.6973 0.03251 0.02442 -0.0737 0.5684 0.7147
4.000 0.7220 0.03291 0.02486 -0.0737 0.5639 0.7211
4.250 0.7571 0.03280 0.02473 -0.0748 0.5608 0.7283
4.500 0.7609 0.03443 0.02655 -0.0726 0.5550 0.7342
4.750 0.7666 0.03604 0.02828 -0.0711 0.5481 0.7417
5.000 0.7978 0.03594 0.02823 -0.0713 0.5448 0.7491
5.250 0.8398 0.03545 0.02772 -0.0727 0.5424 0.7584
5.500 0.7916 0.04036 0.03292 -0.0667 0.5306 0.7637
5.750 0.8292 0.03984 0.03245 -0.0673 0.5276 0.7738
6.000 0.8759 0.03878 0.03144 -0.0686 0.5255 0.7849
6.250 0.7898 0.04620 0.03905 -0.0604 0.5109 0.7911
6.500 0.7888 0.04840 0.04134 -0.0585 0.5045 0.8016
6.750 0.8842 0.04391 0.03693 -0.0624 0.5059 0.8187
7.000 0.8073 0.05127 0.04440 -0.0563 0.4917 0.8295
7.250 0.8691 0.04813 0.04139 -0.0565 0.4911 0.8502
7.500 0.9404 0.04484 0.03822 -0.0583 0.4904 0.8781
7.750 0.8285 0.05507 0.04864 -0.0512 0.4729 0.9122
8.000 0.9183 0.05021 0.04389 -0.0542 0.4731 1.0000
10.000 1.1525 0.04967 0.04367 -0.0562 0.4230 1.0000
10.500 1.1706 0.05140 0.04554 -0.0534 0.4067 1.0000
10.750 0.9741 0.07615 0.07015 -0.0543 0.3734 1.0000
11.000 0.9563 0.08116 0.07519 -0.0549 0.3600 1.0000
11.250 0.9368 0.08671 0.08077 -0.0558 0.3466 1.0000
11.500 0.9920 0.08229 0.07647 -0.0539 0.3443 1.0000
11.750 1.0553 0.07639 0.07072 -0.0516 0.3435 1.0000
12.000 1.1283 0.06858 0.06306 -0.0488 0.3436 1.0000
12.250 1.4268 0.03922 0.03376 -0.0499 0.3421 1.0000
12.500 1.3595 0.04557 0.04031 -0.0452 0.3336 1.0000
12.750 1.3832 0.04469 0.03946 -0.0441 0.3209 1.0000
13.000 1.3980 0.04469 0.03944 -0.0429 0.3072 1.0000
13.250 1.4042 0.04559 0.04032 -0.0417 0.2930 1.0000
13.500 1.4047 0.04720 0.04188 -0.0405 0.2784 1.0000
13.750 1.4020 0.04931 0.04394 -0.0396 0.2636 1.0000
14.000 1.3977 0.05177 0.04633 -0.0388 0.2488 1.0000
14.250 1.3925 0.05448 0.04897 -0.0382 0.2342 1.0000
14.500 1.3877 0.05728 0.05169 -0.0378 0.2198 1.0000
14.750 1.3784 0.06078 0.05517 -0.0377 0.2066 1.0000
15.000 1.3671 0.06475 0.05916 -0.0380 0.1943 1.0000
15.250 1.3602 0.06832 0.06271 -0.0382 0.1820 1.0000
15.500 1.3558 0.07171 0.06604 -0.0384 0.1703 1.0000
15.750 1.3544 0.07476 0.06899 -0.0386 0.1588 1.0000
16.000 1.3566 0.07739 0.07146 -0.0387 0.1472 1.0000
16.250 1.3431 0.08245 0.07670 -0.0401 0.1389 1.0000
16.500 1.3414 0.08585 0.08007 -0.0406 0.1297 1.0000
16.750 1.3470 0.08816 0.08222 -0.0408 0.1200 1.0000
17.000 1.3338 0.09354 0.08783 -0.0425 0.1137 1.0000
17.250 1.3376 0.09627 0.09046 -0.0430 0.1058 1.0000
17.500 1.3307 0.10078 0.09509 -0.0445 0.0997 1.0000
17.750 1.3332 0.10384 0.09812 -0.0452 0.0933 1.0000
18.000 1.3270 0.10837 0.10278 -0.0469 0.0883 1.0000
18.250 1.3333 0.11088 0.10524 -0.0474 0.0827 1.0000
18.500 1.3214 0.11652 0.11111 -0.0499 0.0792 1.0000
18.750 1.3386 0.11718 0.11155 -0.0494 0.0734 1.0000
19.000 1.3210 0.12390 0.11860 -0.0528 0.0714 1.0000
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Polar data table (+)
Polar graphs
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