EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Reynolds number: 50,000 Max Cl/Cd: 30.92 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ste87391-il-50000-n5.txt Download as CSV file: xf-ste87391-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STE 87(-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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4951 0.11345 0.10692 -0.0394 1.0019 0.0517
-9.750 -0.5088 0.10815 0.10170 -0.0404 1.0019 0.0515
-9.500 -0.5256 0.10232 0.09595 -0.0417 1.0019 0.0512
-9.250 -0.5480 0.09548 0.08919 -0.0436 1.0019 0.0505
-9.000 -0.5845 0.08684 0.08059 -0.0469 1.0019 0.0489
-8.750 -0.6638 0.07462 0.06813 -0.0521 1.0019 0.0455
-8.500 -0.6820 0.06918 0.06242 -0.0531 1.0019 0.0454
-8.250 -0.6869 0.06503 0.05804 -0.0535 1.0019 0.0459
-8.000 -0.6849 0.06145 0.05423 -0.0537 1.0019 0.0469
-7.750 -0.6788 0.05793 0.05042 -0.0542 1.0019 0.0480
-7.500 -0.6687 0.05432 0.04640 -0.0548 1.0019 0.0493
-7.250 -0.6545 0.05089 0.04248 -0.0555 1.0019 0.0503
-7.000 -0.6367 0.04788 0.03901 -0.0560 1.0019 0.0512
-6.750 -0.6168 0.04536 0.03606 -0.0562 1.0019 0.0523
-6.500 -0.5934 0.04330 0.03358 -0.0566 1.0013 0.0536
-6.250 -0.5633 0.04160 0.03154 -0.0579 0.9985 0.0555
-5.750 -0.5037 0.03919 0.02882 -0.0610 0.9927 0.0642
-5.500 -0.4729 0.03811 0.02755 -0.0623 0.9896 0.0688
-5.250 -0.4405 0.03719 0.02654 -0.0640 0.9869 0.0753
-5.000 -0.4081 0.03623 0.02556 -0.0658 0.9839 0.0873
-4.750 -0.3763 0.03520 0.02491 -0.0678 0.9805 0.1265
-4.500 -0.3425 0.03506 0.02486 -0.0700 0.9769 0.2002
-4.250 -0.3056 0.03549 0.02531 -0.0732 0.9735 0.2634
-4.000 -0.2771 0.03566 0.02554 -0.0748 0.9684 0.3139
-3.750 -0.2461 0.03571 0.02545 -0.0759 0.9644 0.3368
-3.500 -0.2117 0.03585 0.02545 -0.0776 0.9611 0.3543
-3.250 -0.1859 0.03570 0.02521 -0.0777 0.9558 0.3706
-3.000 -0.1549 0.03573 0.02517 -0.0789 0.9513 0.3894
-2.750 -0.1195 0.03590 0.02529 -0.0808 0.9477 0.4137
-2.500 -0.0940 0.03577 0.02524 -0.0809 0.9419 0.4399
-2.250 -0.0633 0.03580 0.02542 -0.0820 0.9371 0.4777
-2.000 -0.0317 0.03599 0.02591 -0.0827 0.9333 0.5360
-1.750 -0.0206 0.03600 0.02631 -0.0788 0.9257 0.5975
-1.500 -0.0037 0.03657 0.02709 -0.0752 0.9203 0.6727
-1.250 0.0151 0.03695 0.02735 -0.0735 0.9124 0.7389
-1.000 0.0429 0.03754 0.02775 -0.0732 0.9070 0.7853
-0.750 0.0568 0.03771 0.02784 -0.0703 0.8987 0.8164
-0.500 0.0797 0.03798 0.02799 -0.0688 0.8930 0.8466
-0.250 0.0920 0.03794 0.02787 -0.0657 0.8841 0.8724
0.000 0.1159 0.03797 0.02780 -0.0644 0.8785 0.8998
0.250 0.1280 0.03771 0.02750 -0.0615 0.8688 0.9246
0.500 0.1561 0.03761 0.02732 -0.0616 0.8616 0.9536
0.750 0.1883 0.03731 0.02697 -0.0630 0.8519 0.9981
1.000 0.2143 0.03750 0.02705 -0.0637 0.8423 0.9981
1.250 0.2545 0.03777 0.02719 -0.0666 0.8366 0.9981
1.500 0.2790 0.03792 0.02727 -0.0670 0.8258 0.9981
2.000 0.3472 0.03817 0.02738 -0.0705 0.8094 0.9981
2.250 0.3728 0.03827 0.02745 -0.0709 0.7979 0.9981
2.500 0.4006 0.03835 0.02750 -0.0715 0.7866 0.9981
2.750 0.4317 0.03836 0.02749 -0.0725 0.7762 0.9981
3.000 0.4696 0.03816 0.02727 -0.0744 0.7677 0.9981
3.250 0.4967 0.03814 0.02727 -0.0746 0.7549 0.9981
3.500 0.5248 0.03808 0.02723 -0.0750 0.7421 0.9981
3.750 0.5544 0.03795 0.02712 -0.0755 0.7295 0.9981
4.000 0.5859 0.03771 0.02692 -0.0761 0.7175 0.9981
4.250 0.6246 0.03706 0.02631 -0.0774 0.7083 0.9981
4.500 0.6526 0.03684 0.02614 -0.0774 0.6944 0.9981
4.750 0.6810 0.03656 0.02595 -0.0774 0.6804 0.9981
5.000 0.7099 0.03624 0.02569 -0.0773 0.6663 0.9981
5.250 0.7396 0.03588 0.02540 -0.0773 0.6519 0.9981
5.500 0.7701 0.03547 0.02509 -0.0774 0.6369 0.9981
6.000 0.8342 0.03452 0.02426 -0.0777 0.6046 0.9981
6.250 0.8692 0.03391 0.02371 -0.0781 0.5872 0.9981
6.500 0.8967 0.03387 0.02370 -0.0779 0.5655 0.9981
6.750 0.9301 0.03351 0.02334 -0.0782 0.5447 0.9981
7.000 0.9615 0.03338 0.02318 -0.0784 0.5227 0.9981
7.250 0.9897 0.03353 0.02333 -0.0783 0.5001 0.9981
7.500 1.0192 0.03369 0.02342 -0.0784 0.4791 0.9981
7.750 1.0426 0.03426 0.02399 -0.0780 0.4583 0.9981
8.000 1.0674 0.03482 0.02454 -0.0778 0.4395 0.9981
8.250 1.0922 0.03544 0.02517 -0.0775 0.4222 0.9981
8.500 1.1166 0.03613 0.02588 -0.0774 0.4064 0.9981
8.750 1.1407 0.03689 0.02669 -0.0772 0.3918 0.9981
9.000 1.1646 0.03771 0.02758 -0.0770 0.3784 0.9981
9.250 1.1890 0.03854 0.02853 -0.0770 0.3660 0.9981
9.500 1.2153 0.03933 0.02940 -0.0771 0.3545 0.9981
9.750 1.2413 0.04016 0.03034 -0.0772 0.3438 0.9981
10.000 1.2602 0.04130 0.03167 -0.0766 0.3334 0.9981
10.250 1.2832 0.04228 0.03280 -0.0763 0.3235 0.9981
10.500 1.3050 0.04329 0.03395 -0.0759 0.3139 0.9981
10.750 1.3177 0.04465 0.03555 -0.0745 0.3044 0.9981
11.000 1.3370 0.04569 0.03670 -0.0738 0.2949 0.9981
11.250 1.3461 0.04709 0.03830 -0.0720 0.2851 0.9981
11.500 1.3530 0.04859 0.04001 -0.0699 0.2756 0.9981
11.750 1.3649 0.04972 0.04123 -0.0684 0.2655 0.9981
12.000 1.3633 0.05154 0.04333 -0.0656 0.2558 0.9981
12.250 1.3623 0.05332 0.04531 -0.0631 0.2458 0.9981
12.500 1.3633 0.05483 0.04691 -0.0607 0.2353 0.9981
12.750 1.3553 0.05705 0.04934 -0.0580 0.2250 0.9981
13.000 1.3455 0.05959 0.05209 -0.0554 0.2149 0.9981
13.250 1.3377 0.06197 0.05459 -0.0532 0.2043 0.9981
13.500 1.3282 0.06461 0.05735 -0.0513 0.1935 0.9981
13.750 1.3123 0.06848 0.06148 -0.0499 0.1832 0.9981
14.000 1.2977 0.07239 0.06556 -0.0490 0.1720 0.9981
14.250 1.2836 0.07656 0.06986 -0.0486 0.1603 0.9981
14.500 1.2685 0.08124 0.07466 -0.0488 0.1479 0.9981
14.750 1.2532 0.08635 0.07987 -0.0496 0.1352 0.9981
15.000 1.2376 0.09183 0.08543 -0.0509 0.1225 0.9981
15.250 1.2225 0.09748 0.09111 -0.0526 0.1106 0.9981
15.500 1.2067 0.10355 0.09722 -0.0547 0.0993 0.9981
15.750 1.1921 0.10961 0.10331 -0.0569 0.0897 0.9981
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