EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 556 AIRFOIL (e556-il) Reynolds number: 50,000 Max Cl/Cd: 32.53 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e556-il-50000-n5.txt Download as CSV file: xf-e556-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 556 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4604 0.10811 0.10064 -0.0548 1.0000 0.0459
-12.250 -0.4796 0.09995 0.09250 -0.0586 1.0000 0.0451
-12.000 -0.5078 0.09095 0.08347 -0.0632 1.0000 0.0438
-11.750 -0.5377 0.08300 0.07541 -0.0673 1.0000 0.0431
-11.500 -0.5666 0.07615 0.06841 -0.0704 1.0000 0.0423
-11.250 -0.5889 0.07088 0.06297 -0.0722 1.0000 0.0418
-11.000 -0.6023 0.06717 0.05917 -0.0726 1.0000 0.0424
-10.750 -0.6144 0.06390 0.05582 -0.0725 1.0000 0.0431
-10.500 -0.6258 0.06087 0.05266 -0.0718 1.0000 0.0436
-10.250 -0.6368 0.05823 0.04991 -0.0706 1.0000 0.0444
-10.000 -0.6470 0.05588 0.04743 -0.0687 1.0000 0.0452
-9.750 -0.6563 0.05378 0.04519 -0.0663 1.0000 0.0460
-9.500 -0.6606 0.05166 0.04288 -0.0640 1.0000 0.0472
-9.250 -0.6579 0.04977 0.04082 -0.0617 1.0000 0.0489
-9.000 -0.6533 0.04842 0.03953 -0.0594 1.0000 0.0514
-8.750 -0.6501 0.04706 0.03810 -0.0571 1.0000 0.0542
-8.500 -0.6436 0.04573 0.03655 -0.0543 1.0000 0.0579
-8.250 -0.6387 0.04460 0.03551 -0.0516 1.0000 0.0611
-8.000 -0.6368 0.04339 0.03431 -0.0491 1.0000 0.0653
-7.750 -0.6327 0.04224 0.03303 -0.0464 1.0000 0.0706
-7.500 -0.6317 0.04095 0.03186 -0.0443 1.0000 0.0756
-7.250 -0.6276 0.03972 0.03053 -0.0422 1.0000 0.0830
-7.000 -0.6248 0.03823 0.02916 -0.0407 1.0000 0.0903
-6.750 -0.6055 0.03636 0.02732 -0.0425 0.9955 0.1055
-6.500 -0.5782 0.03380 0.02495 -0.0468 0.9878 0.1333
-6.250 -0.5497 0.03050 0.02225 -0.0526 0.9805 0.1968
-5.750 -0.4828 0.03180 0.02432 -0.0551 0.9641 0.3998
-5.500 -0.4507 0.03308 0.02535 -0.0551 0.9553 0.4313
-5.250 -0.4143 0.03408 0.02605 -0.0562 0.9482 0.4582
-5.000 -0.3883 0.03510 0.02690 -0.0546 0.9386 0.4753
-4.750 -0.3579 0.03595 0.02759 -0.0539 0.9310 0.4918
-4.500 -0.3282 0.03622 0.02765 -0.0541 0.9225 0.5067
-4.250 -0.3006 0.03664 0.02795 -0.0530 0.9143 0.5153
-4.000 -0.2678 0.03619 0.02725 -0.0548 0.9066 0.5252
-3.750 -0.2388 0.03592 0.02680 -0.0555 0.8981 0.5321
-3.500 -0.2029 0.03519 0.02581 -0.0585 0.8907 0.5401
-3.250 -0.1751 0.03495 0.02543 -0.0587 0.8820 0.5448
-3.000 -0.1381 0.03430 0.02455 -0.0617 0.8749 0.5517
-2.750 -0.1085 0.03386 0.02395 -0.0629 0.8661 0.5569
-2.500 -0.0740 0.03351 0.02347 -0.0644 0.8591 0.5613
-2.250 -0.0435 0.03307 0.02286 -0.0660 0.8501 0.5669
-2.000 -0.0056 0.03253 0.02215 -0.0688 0.8434 0.5723
-1.750 0.0214 0.03235 0.02190 -0.0689 0.8342 0.5762
-1.500 0.0585 0.03193 0.02136 -0.0711 0.8275 0.5811
-1.250 0.0909 0.03156 0.02083 -0.0732 0.8185 0.5871
-1.000 0.1255 0.03129 0.02052 -0.0743 0.8116 0.5909
-0.750 0.1528 0.03116 0.02033 -0.0747 0.8021 0.5953
-0.500 0.1932 0.03075 0.01980 -0.0775 0.7956 0.6010
-0.250 0.2194 0.03066 0.01968 -0.0777 0.7856 0.6053
0.000 0.2563 0.03037 0.01936 -0.0792 0.7791 0.6099
0.250 0.2827 0.03033 0.01927 -0.0797 0.7688 0.6153
0.500 0.3230 0.02996 0.01884 -0.0820 0.7626 0.6206
0.750 0.3450 0.03005 0.01895 -0.0813 0.7516 0.6249
1.000 0.3863 0.02968 0.01854 -0.0836 0.7459 0.6309
1.250 0.4097 0.02980 0.01866 -0.0835 0.7344 0.6363
1.500 0.4400 0.02971 0.01859 -0.0839 0.7262 0.6411
1.750 0.4712 0.02964 0.01853 -0.0847 0.7171 0.6471
2.000 0.4985 0.02972 0.01862 -0.0849 0.7072 0.6530
2.250 0.5327 0.02953 0.01847 -0.0858 0.6997 0.6587
2.500 0.5573 0.02975 0.01871 -0.0858 0.6888 0.6654
2.750 0.5951 0.02945 0.01844 -0.0871 0.6823 0.6714
3.000 0.6149 0.02979 0.01887 -0.0862 0.6706 0.6780
3.250 0.6432 0.02989 0.01902 -0.0864 0.6612 0.6850
3.500 0.6738 0.02984 0.01906 -0.0867 0.6526 0.6920
3.750 0.6969 0.03016 0.01944 -0.0864 0.6417 0.6998
4.000 0.7335 0.02987 0.01922 -0.0873 0.6346 0.7077
4.250 0.7523 0.03033 0.01980 -0.0863 0.6227 0.7161
4.500 0.7753 0.03056 0.02015 -0.0855 0.6125 0.7244
4.750 0.8088 0.03042 0.02009 -0.0861 0.6040 0.7340
5.000 0.8271 0.03087 0.02067 -0.0849 0.5923 0.7442
5.250 0.8511 0.03102 0.02096 -0.0841 0.5823 0.7545
5.500 0.8808 0.03095 0.02100 -0.0840 0.5727 0.7665
5.750 0.8977 0.03140 0.02161 -0.0825 0.5608 0.7792
6.000 0.9198 0.03158 0.02195 -0.0815 0.5500 0.7937
6.250 0.9492 0.03135 0.02185 -0.0810 0.5403 0.8104
6.500 0.9606 0.03180 0.02250 -0.0785 0.5279 0.8291
6.750 0.9758 0.03205 0.02295 -0.0763 0.5163 0.8534
7.000 0.9970 0.03190 0.02296 -0.0747 0.5056 0.8914
7.250 1.0247 0.03183 0.02302 -0.0747 0.4933 1.0000
7.500 1.0482 0.03244 0.02370 -0.0748 0.4793 1.0000
7.750 1.0705 0.03303 0.02438 -0.0746 0.4653 1.0000
8.000 1.0915 0.03359 0.02500 -0.0740 0.4513 1.0000
8.250 1.1107 0.03414 0.02560 -0.0730 0.4371 1.0000
8.500 1.1286 0.03470 0.02622 -0.0718 0.4227 1.0000
8.750 1.1450 0.03532 0.02691 -0.0704 0.4080 1.0000
9.000 1.1595 0.03601 0.02765 -0.0688 0.3929 1.0000
9.250 1.1724 0.03680 0.02849 -0.0670 0.3778 1.0000
9.500 1.1832 0.03769 0.02944 -0.0651 0.3624 1.0000
9.750 1.1925 0.03870 0.03050 -0.0632 0.3468 1.0000
10.000 1.2003 0.03985 0.03172 -0.0612 0.3312 1.0000
10.250 1.2067 0.04114 0.03305 -0.0593 0.3156 1.0000
10.500 1.2118 0.04258 0.03454 -0.0575 0.3000 1.0000
10.750 1.2159 0.04419 0.03619 -0.0558 0.2847 1.0000
11.000 1.2192 0.04595 0.03798 -0.0542 0.2698 1.0000
11.250 1.2217 0.04786 0.03992 -0.0528 0.2552 1.0000
11.500 1.2240 0.04991 0.04199 -0.0516 0.2412 1.0000
11.750 1.2257 0.05209 0.04420 -0.0505 0.2278 1.0000
12.000 1.2278 0.05433 0.04642 -0.0495 0.2150 1.0000
12.250 1.2271 0.05700 0.04917 -0.0488 0.2028 1.0000
12.500 1.2253 0.05995 0.05220 -0.0483 0.1911 1.0000
12.750 1.2247 0.06285 0.05514 -0.0479 0.1804 1.0000
13.000 1.2260 0.06553 0.05780 -0.0476 0.1704 1.0000
13.250 1.2230 0.06893 0.06131 -0.0476 0.1607 1.0000
13.500 1.2208 0.07237 0.06486 -0.0478 0.1520 1.0000
13.750 1.2238 0.07500 0.06742 -0.0477 0.1435 1.0000
14.000 1.2156 0.07957 0.07225 -0.0486 0.1359 1.0000
14.250 1.2184 0.08241 0.07505 -0.0488 0.1286 1.0000
14.500 1.2096 0.08737 0.08028 -0.0501 0.1223 1.0000
14.750 1.2143 0.08995 0.08276 -0.0503 0.1156 1.0000
15.000 1.2010 0.09596 0.08910 -0.0524 0.1106 1.0000
15.250 1.1998 0.09979 0.09300 -0.0535 0.1052 1.0000
15.500 1.1955 0.10437 0.09768 -0.0551 0.1006 1.0000
15.750 1.1783 0.11161 0.10521 -0.0585 0.0971 1.0000
16.000 1.1724 0.11670 0.11041 -0.0607 0.0930 1.0000
16.250 1.1747 0.12016 0.11387 -0.0619 0.0889 1.0000
16.500 1.1423 0.13149 0.12551 -0.0685 0.0876 1.0000
16.750 1.0884 0.14931 0.14355 -0.0795 0.0871 1.0000
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Polar data table (+)
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