EPPLER 551 AIRFOIL (e551-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 551 AIRFOIL (e551-il) Reynolds number: 100,000 Max Cl/Cd: 47.14 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e551-il-100000-n5.txt Download as CSV file: xf-e551-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 551 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4591 0.11226 0.10689 -0.0586 1.0000 0.0197
-14.250 -0.5165 0.09519 0.08959 -0.0682 1.0000 0.0188
-14.000 -0.5604 0.08399 0.07807 -0.0744 1.0000 0.0183
-13.750 -0.5826 0.07768 0.07156 -0.0774 1.0000 0.0182
-13.500 -0.6008 0.07250 0.06619 -0.0794 1.0000 0.0181
-13.250 -0.6141 0.06825 0.06179 -0.0806 1.0000 0.0182
-13.000 -0.6249 0.06450 0.05788 -0.0813 1.0000 0.0182
-12.750 -0.6328 0.06129 0.05455 -0.0816 1.0000 0.0184
-12.500 -0.6395 0.05829 0.05142 -0.0815 1.0000 0.0185
-12.250 -0.6443 0.05565 0.04865 -0.0811 1.0000 0.0188
-12.000 -0.6479 0.05326 0.04615 -0.0803 1.0000 0.0190
-11.750 -0.6500 0.05110 0.04388 -0.0792 1.0000 0.0192
-11.500 -0.6523 0.04920 0.04188 -0.0777 1.0000 0.0197
-11.250 -0.6560 0.04751 0.04009 -0.0757 1.0000 0.0203
-11.000 -0.6627 0.04604 0.03848 -0.0730 1.0000 0.0210
-10.750 -0.6603 0.04460 0.03700 -0.0715 0.9981 0.0216
-10.500 -0.6355 0.04264 0.03498 -0.0745 0.9894 0.0231
-10.250 -0.6086 0.04092 0.03311 -0.0763 0.9814 0.0244
-10.000 -0.5834 0.03935 0.03145 -0.0774 0.9718 0.0259
-9.750 -0.5604 0.03782 0.02991 -0.0788 0.9616 0.0273
-9.500 -0.5350 0.03635 0.02831 -0.0804 0.9533 0.0298
-9.250 -0.5122 0.03471 0.02669 -0.0825 0.9438 0.0331
-9.000 -0.4896 0.03312 0.02505 -0.0843 0.9339 0.0371
-8.750 -0.4647 0.03147 0.02334 -0.0868 0.9255 0.0428
-8.500 -0.4486 0.02986 0.02169 -0.0879 0.9128 0.0498
-8.250 -0.4355 0.02826 0.02007 -0.0887 0.8999 0.0584
-8.000 -0.4231 0.02665 0.01846 -0.0893 0.8883 0.0705
-7.750 -0.4100 0.02519 0.01702 -0.0894 0.8770 0.0893
-7.500 -0.4019 0.02380 0.01574 -0.0885 0.8647 0.1157
-7.250 -0.3927 0.02219 0.01433 -0.0880 0.8542 0.1621
-7.000 -0.3859 0.02031 0.01293 -0.0872 0.8440 0.2474
-6.750 -0.3709 0.01997 0.01330 -0.0855 0.8341 0.3689
-6.500 -0.3423 0.02011 0.01327 -0.0857 0.8268 0.4167
-6.250 -0.3180 0.02027 0.01319 -0.0852 0.8178 0.4428
-6.000 -0.2892 0.02058 0.01330 -0.0852 0.8107 0.4615
-5.750 -0.2634 0.02087 0.01341 -0.0846 0.8025 0.4764
-5.500 -0.2341 0.02141 0.01389 -0.0840 0.7952 0.4876
-5.250 -0.2062 0.02188 0.01426 -0.0833 0.7882 0.5000
-5.000 -0.1810 0.02209 0.01431 -0.0827 0.7803 0.5121
-4.750 -0.1507 0.02232 0.01442 -0.0825 0.7745 0.5183
-4.500 -0.1279 0.02204 0.01396 -0.0822 0.7660 0.5248
-4.250 -0.0997 0.02177 0.01351 -0.0825 0.7599 0.5288
-4.000 -0.0742 0.02169 0.01332 -0.0821 0.7525 0.5316
-3.750 -0.0472 0.02151 0.01301 -0.0821 0.7458 0.5348
-3.500 -0.0194 0.02125 0.01258 -0.0825 0.7401 0.5388
-3.250 0.0052 0.02095 0.01210 -0.0826 0.7326 0.5429
-3.000 0.0337 0.02076 0.01178 -0.0829 0.7269 0.5456
-2.750 0.0594 0.02069 0.01164 -0.0826 0.7202 0.5480
-2.500 0.0859 0.02057 0.01143 -0.0826 0.7138 0.5507
-2.250 0.1152 0.02039 0.01111 -0.0831 0.7091 0.5536
-2.000 0.1398 0.02029 0.01092 -0.0829 0.7021 0.5571
-1.750 0.1675 0.02011 0.01059 -0.0834 0.6962 0.5611
-1.500 0.1964 0.02003 0.01043 -0.0836 0.6915 0.5633
-1.250 0.2204 0.02003 0.01043 -0.0832 0.6846 0.5656
-1.000 0.2480 0.01997 0.01030 -0.0833 0.6794 0.5683
-0.750 0.2773 0.01989 0.01012 -0.0838 0.6751 0.5715
-0.500 0.3014 0.01990 0.01010 -0.0835 0.6683 0.5753
-0.250 0.3292 0.01985 0.00997 -0.0838 0.6631 0.5788
0.000 0.3586 0.01981 0.00989 -0.0841 0.6592 0.5813
0.250 0.3818 0.01991 0.01003 -0.0836 0.6529 0.5841
0.500 0.4086 0.01993 0.01002 -0.0836 0.6477 0.5873
0.750 0.4382 0.01989 0.00992 -0.0841 0.6436 0.5910
1.000 0.4630 0.01999 0.01000 -0.0840 0.6380 0.5952
1.250 0.4881 0.02008 0.01015 -0.0837 0.6328 0.5982
1.500 0.5163 0.02011 0.01017 -0.0839 0.6286 0.6017
1.750 0.5431 0.02020 0.01026 -0.0839 0.6240 0.6056
2.000 0.5670 0.02035 0.01045 -0.0836 0.6184 0.6097
2.250 0.5943 0.02042 0.01052 -0.0837 0.6139 0.6135
2.500 0.6236 0.02046 0.01057 -0.0840 0.6104 0.6172
2.750 0.6450 0.02070 0.01092 -0.0832 0.6045 0.6216
3.000 0.6705 0.02085 0.01110 -0.0831 0.5995 0.6268
3.250 0.6989 0.02092 0.01120 -0.0833 0.5956 0.6314
3.500 0.7236 0.02109 0.01145 -0.0830 0.5910 0.6359
3.750 0.7456 0.02134 0.01180 -0.0823 0.5853 0.6410
4.000 0.7729 0.02146 0.01196 -0.0824 0.5808 0.6466
4.250 0.8027 0.02150 0.01203 -0.0828 0.5772 0.6516
4.500 0.8199 0.02188 0.01258 -0.0813 0.5707 0.6576
4.750 0.8451 0.02205 0.01282 -0.0811 0.5656 0.6642
5.000 0.8747 0.02207 0.01289 -0.0814 0.5616 0.6706
5.250 0.8921 0.02246 0.01343 -0.0800 0.5549 0.6780
5.500 0.9160 0.02262 0.01371 -0.0794 0.5493 0.6846
5.750 0.9472 0.02261 0.01372 -0.0800 0.5449 0.6928
6.000 0.9609 0.02305 0.01436 -0.0780 0.5374 0.7006
6.250 0.9867 0.02313 0.01454 -0.0776 0.5316 0.7103
6.500 1.0088 0.02331 0.01484 -0.0768 0.5254 0.7198
6.750 1.0268 0.02359 0.01527 -0.0753 0.5181 0.7310
7.000 1.0569 0.02349 0.01525 -0.0755 0.5125 0.7429
7.250 1.0659 0.02397 0.01596 -0.0727 0.5041 0.7552
7.500 1.0921 0.02390 0.01599 -0.0723 0.4974 0.7701
7.750 1.1014 0.02430 0.01661 -0.0695 0.4888 0.7873
8.000 1.1241 0.02422 0.01664 -0.0684 0.4813 0.8089
8.250 1.1285 0.02459 0.01726 -0.0646 0.4722 0.8375
8.500 1.1487 0.02437 0.01718 -0.0629 0.4643 0.8854
8.750 1.1524 0.02486 0.01788 -0.0596 0.4537 1.0000
9.000 1.1668 0.02526 0.01831 -0.0580 0.4438 1.0000
9.250 1.1821 0.02560 0.01867 -0.0564 0.4331 1.0000
9.500 1.1852 0.02646 0.01962 -0.0535 0.4210 1.0000
9.750 1.1920 0.02723 0.02047 -0.0512 0.4087 1.0000
10.000 1.1991 0.02804 0.02133 -0.0491 0.3956 1.0000
10.250 1.2048 0.02899 0.02230 -0.0469 0.3816 1.0000
10.500 1.2088 0.03012 0.02346 -0.0448 0.3665 1.0000
10.750 1.2113 0.03144 0.02479 -0.0428 0.3503 1.0000
11.000 1.2133 0.03291 0.02625 -0.0409 0.3332 1.0000
11.250 1.2147 0.03452 0.02785 -0.0391 0.3158 1.0000
11.500 1.2150 0.03631 0.02959 -0.0375 0.2980 1.0000
11.750 1.2147 0.03826 0.03149 -0.0360 0.2806 1.0000
12.000 1.2133 0.04040 0.03358 -0.0347 0.2637 1.0000
12.250 1.2111 0.04272 0.03585 -0.0335 0.2474 1.0000
12.500 1.2087 0.04518 0.03827 -0.0325 0.2319 1.0000
12.750 1.2062 0.04776 0.04083 -0.0316 0.2170 1.0000
13.000 1.2040 0.05044 0.04351 -0.0310 0.2029 1.0000
13.250 1.2018 0.05321 0.04629 -0.0306 0.1895 1.0000
13.500 1.1999 0.05607 0.04915 -0.0302 0.1768 1.0000
13.750 1.1979 0.05903 0.05211 -0.0301 0.1648 1.0000
14.000 1.1958 0.06208 0.05516 -0.0300 0.1539 1.0000
14.250 1.1934 0.06527 0.05834 -0.0301 0.1432 1.0000
14.500 1.1923 0.06842 0.06155 -0.0303 0.1329 1.0000
14.750 1.1907 0.07170 0.06484 -0.0307 0.1237 1.0000
15.000 1.1879 0.07518 0.06832 -0.0311 0.1154 1.0000
15.250 1.1874 0.07850 0.07174 -0.0317 0.1070 1.0000
15.500 1.1849 0.08211 0.07534 -0.0323 0.1000 1.0000
15.750 1.1837 0.08566 0.07898 -0.0331 0.0928 1.0000
16.000 1.1815 0.08935 0.08270 -0.0340 0.0868 1.0000
16.250 1.1795 0.09314 0.08656 -0.0350 0.0808 1.0000
16.500 1.1776 0.09692 0.09038 -0.0361 0.0758 1.0000
16.750 1.1758 0.10081 0.09436 -0.0373 0.0706 1.0000
17.000 1.1728 0.10484 0.09838 -0.0386 0.0665 1.0000
17.250 1.1721 0.10865 0.10234 -0.0400 0.0619 1.0000
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Polar data table (+)
Polar graphs
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