EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 548 AIRFOIL (e548-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.79 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e548-il-1000000-n5.txt Download as CSV file: xf-e548-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 548 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.7896 0.10171 0.09935 -0.0338 1.0000 0.0024
-16.750 -0.8408 0.08599 0.08338 -0.0426 1.0000 0.0023
-16.500 -0.8642 0.07715 0.07438 -0.0478 1.0000 0.0023
-16.250 -0.8896 0.06890 0.06594 -0.0522 1.0000 0.0023
-16.000 -0.9111 0.06212 0.05897 -0.0552 1.0000 0.0023
-15.750 -0.9224 0.05741 0.05413 -0.0569 1.0000 0.0023
-15.500 -0.9356 0.05283 0.04938 -0.0579 1.0000 0.0023
-15.250 -0.9403 0.04956 0.04600 -0.0583 1.0000 0.0023
-15.000 -0.9443 0.04656 0.04288 -0.0583 1.0000 0.0023
-14.750 -0.9496 0.04358 0.03975 -0.0580 1.0000 0.0023
-14.500 -0.9527 0.04101 0.03706 -0.0574 1.0000 0.0023
-14.250 -0.9530 0.03878 0.03472 -0.0566 1.0000 0.0023
-14.000 -0.9505 0.03686 0.03270 -0.0557 1.0000 0.0023
-13.750 -0.9492 0.03490 0.03062 -0.0546 1.0000 0.0023
-13.500 -0.9472 0.03302 0.02862 -0.0533 1.0000 0.0024
-13.250 -0.9412 0.03156 0.02707 -0.0521 1.0000 0.0024
-13.000 -0.9350 0.03013 0.02555 -0.0507 1.0000 0.0024
-12.750 -0.9176 0.02858 0.02390 -0.0515 0.9986 0.0024
-12.500 -0.9111 0.02731 0.02255 -0.0495 0.9608 0.0024
-12.250 -0.7763 0.02432 0.01919 -0.0753 0.8976 0.0024
-11.750 -0.7465 0.02297 0.01722 -0.0737 0.7744 0.0025
-11.500 -0.7369 0.02206 0.01615 -0.0718 0.7490 0.0026
-11.250 -0.7224 0.02151 0.01548 -0.0706 0.7280 0.0025
-11.000 -0.7114 0.02066 0.01449 -0.0688 0.7096 0.0026
-10.750 -0.7007 0.01978 0.01348 -0.0670 0.6937 0.0028
-10.500 -0.6833 0.01939 0.01301 -0.0660 0.6773 0.0026
-10.250 -0.6712 0.01859 0.01211 -0.0643 0.6648 0.0029
-10.000 -0.6550 0.01809 0.01153 -0.0630 0.6535 0.0029
-9.750 -0.6397 0.01753 0.01090 -0.0616 0.6426 0.0030
-9.500 -0.6229 0.01706 0.01038 -0.0603 0.6330 0.0031
-9.250 -0.6066 0.01659 0.00984 -0.0590 0.6237 0.0031
-9.000 -0.5897 0.01615 0.00935 -0.0577 0.6148 0.0035
-8.750 -0.5735 0.01570 0.00883 -0.0562 0.6067 0.0036
-8.500 -0.5568 0.01528 0.00836 -0.0548 0.5986 0.0037
-8.250 -0.5407 0.01487 0.00790 -0.0533 0.5905 0.0037
-8.000 -0.5250 0.01446 0.00743 -0.0516 0.5828 0.0039
-7.500 -0.4983 0.01372 0.00660 -0.0472 0.5695 0.0046
-7.250 -0.4831 0.01346 0.00630 -0.0452 0.5631 0.0047
-7.000 -0.4642 0.01320 0.00600 -0.0439 0.5574 0.0051
-6.750 -0.4441 0.01294 0.00570 -0.0427 0.5522 0.0055
-6.500 -0.4235 0.01268 0.00541 -0.0416 0.5466 0.0062
-6.250 -0.4024 0.01244 0.00514 -0.0406 0.5416 0.0067
-6.000 -0.3802 0.01221 0.00488 -0.0398 0.5368 0.0077
-5.750 -0.3579 0.01198 0.00463 -0.0390 0.5315 0.0092
-5.250 -0.3118 0.01155 0.00417 -0.0377 0.5223 0.0143
-5.000 -0.2885 0.01130 0.00395 -0.0371 0.5182 0.0208
-4.750 -0.2651 0.01106 0.00374 -0.0365 0.5141 0.0306
-4.250 -0.2192 0.01046 0.00330 -0.0353 0.5071 0.0733
-4.000 -0.1960 0.01012 0.00309 -0.0347 0.5038 0.1064
-3.750 -0.1728 0.00976 0.00287 -0.0342 0.5002 0.1484
-3.500 -0.1530 0.00908 0.00255 -0.0334 0.4965 0.2447
-3.250 -0.1335 0.00827 0.00218 -0.0326 0.4931 0.3675
-3.000 -0.1128 0.00737 0.00178 -0.0320 0.4905 0.5012
-2.750 -0.0879 0.00697 0.00169 -0.0317 0.4878 0.5980
-2.500 -0.0593 0.00697 0.00171 -0.0319 0.4849 0.6240
-2.250 -0.0305 0.00703 0.00174 -0.0321 0.4820 0.6388
-2.000 -0.0018 0.00711 0.00180 -0.0323 0.4791 0.6498
-1.750 0.0269 0.00720 0.00187 -0.0325 0.4764 0.6593
-1.500 0.0561 0.00726 0.00191 -0.0328 0.4740 0.6644
-1.250 0.0853 0.00728 0.00189 -0.0331 0.4713 0.6656
-1.000 0.1144 0.00729 0.00186 -0.0335 0.4688 0.6665
-0.750 0.1434 0.00732 0.00184 -0.0338 0.4663 0.6674
-0.500 0.1723 0.00735 0.00183 -0.0341 0.4639 0.6682
0.000 0.2303 0.00742 0.00183 -0.0348 0.4593 0.6698
0.250 0.2593 0.00743 0.00183 -0.0351 0.4571 0.6708
0.500 0.2883 0.00744 0.00183 -0.0355 0.4550 0.6718
0.750 0.3172 0.00747 0.00185 -0.0358 0.4528 0.6727
1.000 0.3460 0.00750 0.00187 -0.0361 0.4504 0.6735
1.250 0.3746 0.00755 0.00189 -0.0364 0.4479 0.6744
1.500 0.4031 0.00760 0.00193 -0.0366 0.4454 0.6753
1.750 0.4320 0.00764 0.00197 -0.0370 0.4437 0.6761
2.000 0.4609 0.00767 0.00200 -0.0373 0.4417 0.6770
2.250 0.4897 0.00771 0.00205 -0.0377 0.4394 0.6781
2.500 0.5184 0.00775 0.00209 -0.0380 0.4371 0.6792
2.750 0.5470 0.00781 0.00214 -0.0383 0.4345 0.6802
3.000 0.5753 0.00787 0.00220 -0.0385 0.4317 0.6812
3.250 0.6035 0.00795 0.00227 -0.0387 0.4287 0.6821
3.500 0.6323 0.00798 0.00232 -0.0391 0.4260 0.6830
3.750 0.6609 0.00803 0.00238 -0.0394 0.4226 0.6838
4.000 0.6891 0.00810 0.00245 -0.0397 0.4190 0.6847
4.250 0.7171 0.00818 0.00252 -0.0399 0.4155 0.6854
4.500 0.7452 0.00826 0.00260 -0.0401 0.4121 0.6861
4.750 0.7735 0.00830 0.00268 -0.0404 0.4083 0.6872
5.000 0.8014 0.00836 0.00276 -0.0406 0.4035 0.6883
5.250 0.8286 0.00846 0.00286 -0.0407 0.3986 0.6894
5.500 0.8566 0.00853 0.00296 -0.0409 0.3942 0.6905
5.750 0.8842 0.00861 0.00307 -0.0411 0.3885 0.6917
6.000 0.9110 0.00873 0.00319 -0.0411 0.3820 0.6930
6.250 0.9384 0.00883 0.00331 -0.0413 0.3748 0.6943
6.500 0.9647 0.00898 0.00345 -0.0412 0.3659 0.6955
6.750 0.9908 0.00913 0.00360 -0.0412 0.3547 0.6966
7.000 1.0161 0.00934 0.00377 -0.0410 0.3409 0.6978
7.250 1.0402 0.00961 0.00399 -0.0406 0.3245 0.6989
7.500 1.0630 0.00994 0.00425 -0.0400 0.3055 0.7000
7.750 1.0845 0.01034 0.00457 -0.0393 0.2827 0.7011
8.000 1.1040 0.01083 0.00495 -0.0382 0.2582 0.7021
8.250 1.1227 0.01133 0.00535 -0.0369 0.2346 0.7033
8.500 1.1398 0.01188 0.00580 -0.0355 0.2105 0.7048
8.750 1.1567 0.01239 0.00624 -0.0340 0.1903 0.7062
9.000 1.1724 0.01292 0.00670 -0.0323 0.1723 0.7077
9.250 1.1864 0.01347 0.00719 -0.0303 0.1537 0.7092
9.500 1.1969 0.01399 0.00765 -0.0277 0.1385 0.7110
9.750 1.2058 0.01452 0.00814 -0.0248 0.1259 0.7129
10.000 1.2142 0.01512 0.00871 -0.0219 0.1142 0.7147
10.250 1.2221 0.01576 0.00932 -0.0191 0.1041 0.7164
10.500 1.2303 0.01641 0.00996 -0.0165 0.0953 0.7179
11.000 1.2385 0.01817 0.01170 -0.0109 0.0775 0.7214
11.250 1.2409 0.01926 0.01280 -0.0084 0.0701 0.7235
11.500 1.2428 0.02052 0.01407 -0.0061 0.0624 0.7256
11.750 1.2450 0.02191 0.01548 -0.0042 0.0565 0.7278
12.000 1.2461 0.02352 0.01709 -0.0026 0.0509 0.7300
12.250 1.2493 0.02511 0.01871 -0.0013 0.0462 0.7322
12.500 1.2498 0.02699 0.02062 -0.0001 0.0416 0.7342
13.000 1.2514 0.03097 0.02466 0.0019 0.0334 0.7387
13.250 1.2521 0.03307 0.02680 0.0026 0.0305 0.7412
13.500 1.2524 0.03526 0.02903 0.0032 0.0271 0.7439
13.750 1.2522 0.03754 0.03135 0.0038 0.0246 0.7466
14.000 1.2543 0.03968 0.03354 0.0041 0.0227 0.7496
14.250 1.2533 0.04218 0.03607 0.0044 0.0202 0.7521
14.500 1.2527 0.04468 0.03862 0.0046 0.0177 0.7552
14.750 1.2544 0.04705 0.04105 0.0047 0.0165 0.7585
15.000 1.2543 0.04969 0.04374 0.0046 0.0145 0.7617
15.250 1.2567 0.05212 0.04623 0.0044 0.0135 0.7650
15.500 1.2581 0.05473 0.04889 0.0041 0.0122 0.7682
15.750 1.2595 0.05740 0.05162 0.0038 0.0113 0.7718
16.000 1.2598 0.06021 0.05448 0.0033 0.0096 0.7759
16.250 1.2616 0.06294 0.05729 0.0028 0.0091 0.7800
16.500 1.2637 0.06572 0.06013 0.0022 0.0083 0.7842
16.750 1.2656 0.06853 0.06301 0.0015 0.0077 0.7890
17.000 1.2651 0.07170 0.06626 0.0006 0.0066 0.7943
17.250 1.2677 0.07452 0.06916 -0.0002 0.0062 0.7999
17.500 1.2683 0.07767 0.07240 -0.0011 0.0058 0.8060
17.750 1.2687 0.08089 0.07569 -0.0022 0.0052 0.8135
18.000 1.2694 0.08412 0.07902 -0.0033 0.0049 0.8216
18.250 1.2696 0.08741 0.08241 -0.0044 0.0044 0.8318
18.500 1.2680 0.09102 0.08613 -0.0057 0.0041 0.8450
19.000 1.2693 0.09808 0.09364 -0.0090 0.0035 0.9566
19.250 1.2690 0.10165 0.09729 -0.0106 0.0034 1.0000
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Polar data table (+)
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