EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 100,000 Max Cl/Cd: 50.42 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ec863914-il-100000.txt Download as CSV file: xf-ec863914-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5070 0.10159 0.09736 -0.0397 1.0000 0.0595
-9.000 -0.5186 0.09650 0.09232 -0.0401 1.0000 0.0563
-8.750 -0.6500 0.07655 0.07226 -0.0534 1.0000 0.0506
-8.500 -0.6805 0.07327 0.06879 -0.0544 1.0000 0.0500
-8.250 -0.6779 0.06942 0.06494 -0.0533 1.0000 0.0484
-8.000 -0.6893 0.06434 0.05971 -0.0551 1.0000 0.0476
-7.750 -0.6928 0.05926 0.05442 -0.0566 1.0000 0.0454
-7.500 -0.6903 0.05369 0.04840 -0.0598 1.0000 0.0449
-7.250 -0.6763 0.04784 0.04184 -0.0634 1.0000 0.0423
-7.000 -0.6514 0.04304 0.03617 -0.0668 1.0000 0.0403
-6.750 -0.6246 0.04066 0.03323 -0.0680 1.0000 0.0388
-6.500 -0.5991 0.03920 0.03145 -0.0684 1.0000 0.0380
-6.250 -0.5746 0.03701 0.02899 -0.0686 1.0000 0.0376
-6.000 -0.5506 0.03495 0.02677 -0.0685 1.0000 0.0374
-5.750 -0.5268 0.03338 0.02509 -0.0681 1.0000 0.0374
-5.500 -0.5029 0.03215 0.02380 -0.0678 1.0000 0.0375
-5.250 -0.4776 0.03108 0.02271 -0.0678 1.0000 0.0379
-5.000 -0.4472 0.02969 0.02124 -0.0694 1.0000 0.0390
-4.750 -0.4128 0.02864 0.02006 -0.0720 1.0000 0.0411
-4.500 -0.3792 0.02793 0.01918 -0.0742 1.0000 0.0447
-4.250 -0.3451 0.02729 0.01843 -0.0762 1.0000 0.0526
-4.000 -0.3002 0.02616 0.01833 -0.0815 1.0000 0.2295
-3.750 -0.2683 0.02640 0.01859 -0.0837 1.0000 0.2818
-3.500 -0.2399 0.02661 0.01878 -0.0849 1.0000 0.3109
-3.250 -0.2128 0.02682 0.01898 -0.0856 1.0000 0.3338
-3.000 -0.1870 0.02701 0.01920 -0.0861 1.0000 0.3510
-2.750 -0.1601 0.02726 0.01951 -0.0869 1.0000 0.3779
-2.500 -0.1343 0.02750 0.01984 -0.0873 1.0000 0.4009
-2.250 -0.1076 0.02773 0.02026 -0.0881 1.0000 0.4364
-2.000 -0.0823 0.02799 0.02099 -0.0883 1.0000 0.4982
-1.750 -0.0714 0.02862 0.02215 -0.0849 1.0000 0.5606
-1.500 -0.0629 0.02959 0.02327 -0.0810 1.0000 0.6237
-1.250 -0.0522 0.03070 0.02434 -0.0778 1.0000 0.6674
-1.000 -0.0294 0.03251 0.02607 -0.0761 0.9941 0.6979
-0.750 0.0331 0.03489 0.02826 -0.0797 0.9582 0.7286
-0.500 0.0631 0.03587 0.02917 -0.0788 0.9436 0.7494
-0.250 0.0893 0.03637 0.02957 -0.0777 0.9305 0.7683
0.000 0.1096 0.03662 0.02977 -0.0755 0.9181 0.7837
0.250 0.1304 0.03676 0.02987 -0.0735 0.9059 0.7988
0.500 0.1516 0.03682 0.02988 -0.0716 0.8942 0.8136
0.750 0.1752 0.03681 0.02983 -0.0703 0.8831 0.8279
1.000 0.2030 0.03673 0.02971 -0.0697 0.8733 0.8418
1.250 0.2335 0.03652 0.02944 -0.0696 0.8639 0.8553
1.500 0.2591 0.03627 0.02916 -0.0690 0.8522 0.8671
1.750 0.2830 0.03588 0.02876 -0.0680 0.8410 0.8781
2.000 0.3092 0.03538 0.02825 -0.0671 0.8312 0.8896
2.250 0.3398 0.03463 0.02749 -0.0666 0.8231 0.9040
2.500 0.3577 0.03391 0.02677 -0.0642 0.8111 0.9197
2.750 0.3756 0.03296 0.02583 -0.0615 0.7994 0.9351
3.000 0.3992 0.03197 0.02486 -0.0599 0.7886 0.9494
3.250 0.4381 0.03062 0.02353 -0.0605 0.7816 0.9631
3.500 0.4730 0.02975 0.02269 -0.0613 0.7694 0.9733
3.750 0.5138 0.02895 0.02196 -0.0633 0.7580 0.9792
4.000 0.5700 0.02748 0.02054 -0.0670 0.7530 0.9835
4.250 0.6092 0.02652 0.01965 -0.0685 0.7407 0.9900
4.750 0.6955 0.02406 0.01735 -0.0721 0.7195 1.0000
5.000 0.7495 0.02241 0.01579 -0.0752 0.7102 1.0000
5.250 0.7917 0.02143 0.01488 -0.0769 0.6913 1.0000
5.500 0.8425 0.02023 0.01372 -0.0798 0.6682 1.0000
5.750 0.8919 0.01939 0.01283 -0.0826 0.6343 1.0000
6.000 0.9366 0.01906 0.01233 -0.0850 0.5904 1.0000
6.250 0.9726 0.01929 0.01233 -0.0863 0.5419 1.0000
6.500 1.0029 0.01990 0.01265 -0.0870 0.4971 1.0000
6.750 1.0317 0.02070 0.01318 -0.0877 0.4590 1.0000
7.000 1.0602 0.02157 0.01387 -0.0884 0.4279 1.0000
7.250 1.0929 0.02249 0.01458 -0.0899 0.4029 1.0000
7.500 1.1228 0.02339 0.01549 -0.0909 0.3818 1.0000
7.750 1.1559 0.02432 0.01637 -0.0925 0.3641 1.0000
8.000 1.1911 0.02529 0.01734 -0.0945 0.3495 1.0000
8.250 1.2270 0.02631 0.01840 -0.0966 0.3370 1.0000
8.500 1.2632 0.02736 0.01951 -0.0988 0.3256 1.0000
8.750 1.3053 0.02850 0.02069 -0.1020 0.3153 1.0000
9.000 1.3333 0.02956 0.02202 -0.1027 0.3062 1.0000
9.250 1.3642 0.03065 0.02325 -0.1040 0.2963 1.0000
9.500 1.3833 0.03138 0.02405 -0.1032 0.2833 1.0000
9.750 1.3897 0.03188 0.02461 -0.1005 0.2684 1.0000
10.000 1.3882 0.03238 0.02519 -0.0966 0.2529 1.0000
10.250 1.3838 0.03303 0.02594 -0.0926 0.2370 1.0000
10.500 1.3812 0.03392 0.02695 -0.0892 0.2213 1.0000
10.750 1.3799 0.03503 0.02823 -0.0862 0.2052 1.0000
11.000 1.3746 0.03649 0.02991 -0.0831 0.1829 1.0000
11.250 1.3607 0.03916 0.03235 -0.0797 0.1028 1.0000
11.500 1.3415 0.04387 0.03637 -0.0764 0.0527 1.0000
11.750 1.3339 0.04770 0.04024 -0.0743 0.0429 1.0000
12.000 1.3280 0.05142 0.04412 -0.0728 0.0384 1.0000
12.250 1.3181 0.05566 0.04851 -0.0715 0.0361 1.0000
12.500 1.3149 0.05942 0.05253 -0.0709 0.0342 1.0000
12.750 1.3107 0.06349 0.05681 -0.0706 0.0327 1.0000
13.000 1.3063 0.06772 0.06122 -0.0707 0.0315 1.0000
13.250 1.3028 0.07200 0.06566 -0.0710 0.0304 1.0000
13.500 1.3004 0.07624 0.07000 -0.0715 0.0293 1.0000
13.750 1.2999 0.08024 0.07404 -0.0717 0.0280 1.0000
14.000 1.3088 0.08319 0.07703 -0.0710 0.0266 1.0000
14.250 1.3136 0.08687 0.08094 -0.0717 0.0256 1.0000
14.500 1.3194 0.09050 0.08478 -0.0724 0.0248 1.0000
14.750 1.3253 0.09421 0.08870 -0.0730 0.0242 1.0000
15.000 1.3294 0.09834 0.09305 -0.0738 0.0239 1.0000
15.250 1.3301 0.10300 0.09797 -0.0751 0.0238 1.0000
15.500 1.3266 0.10834 0.10357 -0.0772 0.0237 1.0000
15.750 1.3196 0.11434 0.10985 -0.0800 0.0238 1.0000
16.000 1.3100 0.12093 0.11671 -0.0836 0.0240 1.0000
16.250 1.2976 0.12819 0.12424 -0.0882 0.0241 1.0000
16.500 1.2837 0.13608 0.13239 -0.0936 0.0243 1.0000
16.750 1.2679 0.14479 0.14134 -0.0999 0.0246 1.0000
17.000 1.2519 0.15401 0.15079 -0.1070 0.0249 1.0000
17.250 1.2327 0.16452 0.16150 -0.1152 0.0253 1.0000
17.500 1.2161 0.17500 0.17213 -0.1233 0.0258 1.0000
17.750 1.1974 0.18682 0.18407 -0.1323 0.0263 1.0000
18.000 1.1847 0.19747 0.19475 -0.1398 0.0269 1.0000
18.250 0.8077 0.20596 0.20355 -0.1123 0.0439 1.0000
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Polar data table (+)
Polar graphs
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