EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 50,000 Max Cl/Cd: 32.31 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ec863914-il-50000-n5.txt Download as CSV file: xf-ec863914-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EC 86(-3)-914 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4710 0.10998 0.10349 -0.0432 1.0000 0.0264
-10.000 -0.4842 0.10418 0.09774 -0.0447 1.0000 0.0260
-9.750 -0.5002 0.09802 0.09160 -0.0466 1.0000 0.0255
-9.500 -0.5194 0.09156 0.08514 -0.0489 1.0000 0.0251
-9.250 -0.5408 0.08535 0.07888 -0.0512 1.0000 0.0248
-9.000 -0.5637 0.07985 0.07332 -0.0530 1.0000 0.0244
-8.750 -0.5887 0.07527 0.06866 -0.0535 1.0000 0.0242
-8.500 -0.6161 0.07151 0.06484 -0.0527 1.0000 0.0240
-8.250 -0.6380 0.06762 0.06082 -0.0527 1.0000 0.0239
-8.000 -0.6505 0.06350 0.05649 -0.0538 1.0000 0.0237
-7.750 -0.6541 0.05962 0.05231 -0.0550 1.0000 0.0236
-7.500 -0.6507 0.05609 0.04846 -0.0559 1.0000 0.0235
-7.250 -0.6417 0.05292 0.04495 -0.0566 1.0000 0.0235
-7.000 -0.6286 0.05018 0.04188 -0.0570 1.0000 0.0236
-6.750 -0.6128 0.04778 0.03919 -0.0572 1.0000 0.0238
-6.500 -0.5953 0.04572 0.03686 -0.0572 1.0000 0.0239
-6.250 -0.5765 0.04391 0.03482 -0.0572 1.0000 0.0243
-6.000 -0.5564 0.04229 0.03294 -0.0573 1.0000 0.0245
-5.750 -0.5348 0.04076 0.03118 -0.0577 1.0000 0.0251
-5.500 -0.5118 0.03944 0.02964 -0.0583 1.0000 0.0256
-5.250 -0.4812 0.03826 0.02819 -0.0603 0.9980 0.0266
-5.000 -0.4456 0.03736 0.02696 -0.0632 0.9947 0.0284
-4.750 -0.4096 0.03605 0.02545 -0.0665 0.9914 0.0311
-4.500 -0.3733 0.03520 0.02430 -0.0694 0.9882 0.0359
-4.250 -0.3367 0.03440 0.02336 -0.0720 0.9850 0.0441
-4.000 -0.2970 0.03279 0.02287 -0.0770 0.9821 0.2103
-3.750 -0.2574 0.03277 0.02290 -0.0808 0.9782 0.2751
-3.500 -0.2199 0.03296 0.02298 -0.0835 0.9746 0.3010
-3.250 -0.1883 0.03298 0.02288 -0.0848 0.9697 0.3172
-3.000 -0.1533 0.03306 0.02290 -0.0871 0.9652 0.3458
-2.750 -0.1143 0.03321 0.02322 -0.0901 0.9616 0.3921
-2.500 -0.0849 0.03314 0.02347 -0.0911 0.9560 0.4468
-2.250 -0.0590 0.03352 0.02417 -0.0903 0.9507 0.4926
-2.000 -0.0446 0.03400 0.02489 -0.0868 0.9435 0.5283
-1.750 -0.0250 0.03480 0.02576 -0.0841 0.9372 0.5702
-1.500 -0.0021 0.03538 0.02618 -0.0830 0.9297 0.6152
-1.250 0.0322 0.03614 0.02673 -0.0843 0.9240 0.6565
-1.000 0.0570 0.03668 0.02711 -0.0838 0.9163 0.6841
-0.750 0.0838 0.03731 0.02760 -0.0830 0.9104 0.7055
-0.500 0.1044 0.03764 0.02783 -0.0816 0.9017 0.7249
-0.250 0.1293 0.03801 0.02806 -0.0810 0.8940 0.7434
0.000 0.1560 0.03833 0.02829 -0.0804 0.8875 0.7594
0.250 0.1764 0.03850 0.02839 -0.0790 0.8783 0.7740
0.500 0.1978 0.03862 0.02844 -0.0777 0.8696 0.7881
0.750 0.2222 0.03870 0.02844 -0.0768 0.8619 0.8018
1.000 0.2441 0.03869 0.02840 -0.0754 0.8531 0.8178
1.250 0.2594 0.03857 0.02828 -0.0727 0.8428 0.8355
1.500 0.2727 0.03830 0.02799 -0.0694 0.8325 0.8541
1.750 0.2921 0.03796 0.02764 -0.0673 0.8233 0.8732
2.000 0.3156 0.03759 0.02725 -0.0662 0.8137 0.8888
2.250 0.3361 0.03726 0.02692 -0.0649 0.8018 0.9000
2.500 0.3600 0.03692 0.02658 -0.0643 0.7901 0.9088
2.750 0.3907 0.03657 0.02623 -0.0649 0.7795 0.9159
3.000 0.4265 0.03613 0.02581 -0.0662 0.7696 0.9210
3.250 0.4561 0.03591 0.02561 -0.0668 0.7563 0.9255
3.500 0.4861 0.03558 0.02532 -0.0673 0.7431 0.9295
3.750 0.5187 0.03519 0.02497 -0.0682 0.7298 0.9333
4.000 0.5530 0.03471 0.02457 -0.0691 0.7164 0.9370
4.250 0.5866 0.03408 0.02401 -0.0697 0.7027 0.9406
4.500 0.6207 0.03345 0.02348 -0.0703 0.6883 0.9441
4.750 0.6542 0.03288 0.02300 -0.0709 0.6725 0.9478
5.000 0.6873 0.03230 0.02253 -0.0713 0.6555 0.9517
5.250 0.7225 0.03163 0.02194 -0.0720 0.6375 0.9557
5.500 0.7584 0.03102 0.02140 -0.0727 0.6175 0.9596
5.750 0.7923 0.03060 0.02107 -0.0733 0.5937 0.9642
6.000 0.8284 0.03012 0.02063 -0.0742 0.5681 0.9700
6.500 0.8974 0.02957 0.02002 -0.0756 0.5114 1.0000
6.750 0.9303 0.02985 0.02021 -0.0765 0.4825 1.0000
7.000 0.9601 0.03039 0.02069 -0.0772 0.4550 1.0000
7.250 0.9880 0.03111 0.02141 -0.0778 0.4301 1.0000
7.500 1.0175 0.03184 0.02207 -0.0785 0.4085 1.0000
7.750 1.0451 0.03272 0.02298 -0.0792 0.3885 1.0000
8.000 1.0744 0.03360 0.02390 -0.0801 0.3713 1.0000
8.250 1.1051 0.03450 0.02486 -0.0813 0.3560 1.0000
8.500 1.1366 0.03541 0.02589 -0.0825 0.3422 1.0000
8.750 1.1700 0.03632 0.02690 -0.0840 0.3299 1.0000
9.000 1.2047 0.03728 0.02799 -0.0856 0.3191 1.0000
9.250 1.2343 0.03842 0.02938 -0.0867 0.3087 1.0000
9.500 1.2670 0.03952 0.03070 -0.0881 0.2994 1.0000
9.750 1.2979 0.04073 0.03215 -0.0893 0.2907 1.0000
10.000 1.3267 0.04209 0.03380 -0.0902 0.2828 1.0000
10.250 1.3566 0.04336 0.03530 -0.0912 0.2748 1.0000
10.500 1.3769 0.04496 0.03727 -0.0910 0.2671 1.0000
10.750 1.4057 0.04620 0.03872 -0.0918 0.2588 1.0000
11.000 1.4071 0.04787 0.04075 -0.0892 0.2486 1.0000
11.250 1.4063 0.04930 0.04238 -0.0864 0.2365 1.0000
11.500 1.3984 0.05086 0.04416 -0.0832 0.2231 1.0000
11.750 1.3842 0.05285 0.04628 -0.0798 0.2085 1.0000
12.000 1.3673 0.05541 0.04897 -0.0769 0.1932 1.0000
12.250 1.3501 0.05858 0.05227 -0.0749 0.1764 1.0000
12.500 1.3342 0.06229 0.05607 -0.0738 0.1581 1.0000
12.750 1.3235 0.06641 0.06044 -0.0736 0.1366 1.0000
13.000 1.3139 0.07097 0.06518 -0.0741 0.1088 1.0000
13.250 1.2986 0.07651 0.07060 -0.0750 0.0809 1.0000
13.500 1.2804 0.08298 0.07695 -0.0767 0.0656 1.0000
13.750 1.2625 0.08993 0.08392 -0.0789 0.0566 1.0000
14.000 1.2450 0.09722 0.09129 -0.0818 0.0516 1.0000
14.250 1.2290 0.10460 0.09882 -0.0851 0.0474 1.0000
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Polar data table (+)
Polar graphs
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