EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Reynolds number: 100,000 Max Cl/Cd: 51.34 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ste87391-il-100000.txt Download as CSV file: xf-ste87391-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.6712 0.06653 0.06201 -0.0480 1.0019 0.0759
-7.250 -0.6777 0.04814 0.04139 -0.0580 1.0019 0.0610
-7.000 -0.6574 0.04480 0.03779 -0.0584 1.0019 0.0602
-6.750 -0.6341 0.04155 0.03405 -0.0593 1.0019 0.0596
-6.500 -0.6092 0.03892 0.03093 -0.0599 1.0019 0.0594
-6.250 -0.5835 0.03686 0.02843 -0.0603 1.0019 0.0601
-6.000 -0.5590 0.03531 0.02668 -0.0605 1.0019 0.0624
-5.750 -0.5347 0.03413 0.02538 -0.0604 1.0019 0.0649
-5.500 -0.5091 0.03300 0.02397 -0.0602 1.0019 0.0666
-5.250 -0.4846 0.03194 0.02298 -0.0601 1.0019 0.0688
-5.000 -0.4591 0.03116 0.02217 -0.0601 1.0019 0.0720
-4.750 -0.4326 0.03042 0.02151 -0.0605 1.0019 0.0770
-4.500 -0.4046 0.02982 0.02095 -0.0614 1.0019 0.0859
-4.250 -0.3732 0.02913 0.02040 -0.0629 1.0019 0.1027
-4.000 -0.3377 0.02860 0.02062 -0.0657 1.0019 0.2321
-3.750 -0.3138 0.02903 0.02099 -0.0660 1.0019 0.2713
-3.500 -0.2900 0.02936 0.02124 -0.0662 1.0019 0.2959
-3.250 -0.2664 0.02974 0.02167 -0.0666 1.0019 0.3270
-3.000 -0.2430 0.03010 0.02214 -0.0668 1.0019 0.3571
-2.750 -0.2186 0.03036 0.02242 -0.0671 1.0019 0.3801
-2.500 -0.1931 0.03059 0.02264 -0.0676 1.0019 0.3984
-2.250 -0.1674 0.03086 0.02293 -0.0681 1.0019 0.4180
-2.000 -0.1417 0.03114 0.02332 -0.0686 1.0019 0.4423
-1.750 -0.1154 0.03145 0.02387 -0.0692 1.0019 0.4771
-1.500 -0.0870 0.03176 0.02466 -0.0700 1.0019 0.5456
-1.250 -0.0705 0.03264 0.02633 -0.0667 0.9990 0.6813
-1.000 -0.0380 0.03471 0.02834 -0.0666 0.9906 0.7882
-0.750 -0.0168 0.03584 0.02941 -0.0642 0.9769 0.8302
-0.500 0.0220 0.03638 0.02980 -0.0638 0.9415 0.8701
-0.250 0.0438 0.03628 0.02961 -0.0611 0.9222 0.9013
0.000 0.0584 0.03596 0.02921 -0.0576 0.9083 0.9299
0.250 0.0793 0.03565 0.02883 -0.0558 0.8958 0.9603
0.500 0.1147 0.03539 0.02848 -0.0576 0.8824 0.9981
0.750 0.1596 0.03580 0.02875 -0.0614 0.8737 0.9981
1.000 0.1913 0.03592 0.02879 -0.0631 0.8618 0.9981
1.250 0.2274 0.03612 0.02889 -0.0653 0.8513 0.9981
1.500 0.2753 0.03632 0.02900 -0.0692 0.8442 0.9981
1.750 0.3061 0.03634 0.02896 -0.0705 0.8322 0.9981
2.000 0.3430 0.03634 0.02892 -0.0725 0.8221 0.9981
2.250 0.3905 0.03611 0.02864 -0.0760 0.8148 0.9981
2.500 0.4221 0.03595 0.02845 -0.0771 0.8027 0.9981
2.750 0.4754 0.03533 0.02780 -0.0810 0.7980 0.9981
3.000 0.5041 0.03507 0.02754 -0.0815 0.7850 0.9981
3.250 0.5364 0.03474 0.02724 -0.0823 0.7732 0.9981
3.500 0.5849 0.03382 0.02632 -0.0852 0.7677 0.9981
3.750 0.6144 0.03348 0.02601 -0.0856 0.7548 0.9981
4.000 0.6645 0.03223 0.02481 -0.0884 0.7503 0.9981
4.250 0.6933 0.03179 0.02442 -0.0885 0.7367 0.9981
4.500 0.7437 0.03019 0.02288 -0.0910 0.7328 0.9981
4.750 0.7723 0.02960 0.02235 -0.0908 0.7187 0.9981
5.000 0.8233 0.02766 0.02049 -0.0931 0.7147 0.9981
5.250 0.8550 0.02684 0.01974 -0.0932 0.6997 0.9981
5.500 0.8936 0.02567 0.01864 -0.0940 0.6853 0.9981
5.750 0.9396 0.02419 0.01722 -0.0959 0.6696 0.9981
6.000 0.9868 0.02288 0.01592 -0.0980 0.6473 0.9981
6.250 1.0421 0.02159 0.01452 -0.1015 0.6181 0.9981
6.500 1.0803 0.02136 0.01413 -0.1028 0.5808 0.9981
6.750 1.1106 0.02164 0.01423 -0.1031 0.5432 0.9981
7.000 1.1381 0.02217 0.01456 -0.1032 0.5093 0.9981
7.250 1.1658 0.02282 0.01499 -0.1033 0.4801 0.9981
7.500 1.1931 0.02358 0.01558 -0.1036 0.4550 0.9981
7.750 1.2186 0.02438 0.01630 -0.1036 0.4336 0.9981
8.000 1.2469 0.02521 0.01702 -0.1042 0.4151 0.9981
8.250 1.2704 0.02603 0.01788 -0.1039 0.3989 0.9981
8.500 1.2952 0.02691 0.01881 -0.1039 0.3845 0.9981
8.750 1.3247 0.02781 0.01969 -0.1047 0.3715 0.9981
9.000 1.3508 0.02867 0.02057 -0.1049 0.3592 0.9981
9.250 1.3722 0.02962 0.02165 -0.1044 0.3479 0.9981
9.500 1.4041 0.03053 0.02249 -0.1056 0.3359 0.9981
9.750 1.4137 0.03139 0.02359 -0.1030 0.3255 0.9981
10.000 1.4365 0.03228 0.02448 -0.1027 0.3142 0.9981
10.250 1.4471 0.03307 0.02539 -0.1004 0.3033 0.9981
10.500 1.4582 0.03396 0.02639 -0.0982 0.2923 0.9981
10.750 1.4701 0.03463 0.02696 -0.0962 0.2792 0.9981
11.000 1.4635 0.03545 0.02801 -0.0913 0.2680 0.9981
11.250 1.4606 0.03631 0.02893 -0.0873 0.2556 0.9981
11.500 1.4572 0.03720 0.02979 -0.0833 0.2428 0.9981
11.750 1.4505 0.03833 0.03107 -0.0792 0.2308 0.9981
12.000 1.4468 0.03963 0.03255 -0.0756 0.2192 0.9981
12.250 1.4439 0.04102 0.03405 -0.0724 0.2076 0.9981
12.500 1.4380 0.04265 0.03579 -0.0691 0.1947 0.9981
12.750 1.4294 0.04464 0.03796 -0.0659 0.1786 0.9981
13.000 1.4173 0.04720 0.04060 -0.0629 0.1570 0.9981
13.250 1.3998 0.05084 0.04417 -0.0601 0.1188 0.9981
13.500 1.3758 0.05561 0.04861 -0.0574 0.0900 0.9981
13.750 1.3522 0.06076 0.05360 -0.0553 0.0739 0.9981
14.000 1.3330 0.06575 0.05858 -0.0539 0.0649 0.9981
14.250 1.3167 0.07065 0.06352 -0.0531 0.0592 0.9981
14.500 1.3028 0.07545 0.06840 -0.0527 0.0547 0.9981
14.750 1.2915 0.08000 0.07299 -0.0525 0.0516 0.9981
15.000 1.2836 0.08415 0.07718 -0.0524 0.0486 0.9981
15.250 1.2800 0.08769 0.08077 -0.0520 0.0459 0.9981
15.500 1.2815 0.09031 0.08331 -0.0514 0.0435 0.9981
15.750 1.2843 0.09304 0.08615 -0.0508 0.0410 0.9981
16.000 1.2917 0.09485 0.08789 -0.0499 0.0387 0.9981
16.250 1.2939 0.09784 0.09105 -0.0499 0.0369 0.9981
16.500 1.3051 0.09921 0.09232 -0.0490 0.0349 0.9981
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