EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Reynolds number: 50,000 Max Cl/Cd: 32.23 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ste87391-il-50000.txt Download as CSV file: xf-ste87391-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4601 0.11485 0.10879 -0.0142 1.0019 0.2636
-7.500 -0.5655 0.09704 0.09123 -0.0285 1.0019 0.1414
-7.250 -0.5964 0.08715 0.08134 -0.0352 1.0019 0.1299
-7.000 -0.6221 0.07573 0.06964 -0.0426 1.0019 0.1204
-6.750 -0.6311 0.06310 0.05618 -0.0509 1.0019 0.1121
-6.500 -0.6167 0.05803 0.05077 -0.0525 1.0019 0.1109
-6.250 -0.5969 0.05248 0.04461 -0.0553 1.0019 0.1100
-6.000 -0.5711 0.04754 0.03887 -0.0581 1.0019 0.1114
-5.750 -0.5478 0.04524 0.03640 -0.0585 1.0019 0.1157
-5.500 -0.5198 0.04244 0.03303 -0.0598 1.0019 0.1210
-5.250 -0.4942 0.04051 0.03094 -0.0600 1.0019 0.1263
-5.000 -0.4672 0.03877 0.02895 -0.0602 1.0019 0.1350
-4.750 -0.4418 0.03775 0.02794 -0.0602 1.0019 0.1501
-4.500 -0.4146 0.03665 0.02688 -0.0604 1.0019 0.1764
-4.250 -0.3839 0.03552 0.02627 -0.0613 1.0019 0.2697
-4.000 -0.3596 0.03555 0.02643 -0.0613 1.0019 0.3433
-3.750 -0.3423 0.03590 0.02710 -0.0596 1.0019 0.3971
-3.500 -0.3210 0.03589 0.02710 -0.0587 1.0019 0.4377
-3.250 -0.2973 0.03555 0.02669 -0.0584 1.0019 0.4643
-3.000 -0.2726 0.03524 0.02630 -0.0584 1.0019 0.4875
-2.750 -0.2479 0.03500 0.02599 -0.0583 1.0019 0.5110
-2.500 -0.2246 0.03483 0.02587 -0.0579 1.0019 0.5365
-2.250 -0.2028 0.03479 0.02595 -0.0570 1.0019 0.5662
-2.000 -0.1830 0.03491 0.02622 -0.0555 1.0019 0.6050
-1.750 -0.1718 0.03527 0.02687 -0.0516 1.0019 0.6479
-1.500 -0.1670 0.03585 0.02765 -0.0461 1.0019 0.7011
-1.250 -0.1653 0.03641 0.02830 -0.0397 1.0019 0.7765
-1.000 -0.1733 0.03633 0.02824 -0.0309 1.0019 0.8598
-0.750 -0.1856 0.03518 0.02710 -0.0217 1.0019 0.9442
-0.500 -0.1720 0.03397 0.02577 -0.0214 1.0019 0.9981
-0.250 -0.1460 0.03442 0.02590 -0.0238 1.0019 0.9981
0.000 -0.1206 0.03507 0.02628 -0.0257 1.0019 0.9981
0.250 -0.0956 0.03582 0.02682 -0.0274 1.0019 0.9981
0.500 -0.0711 0.03666 0.02745 -0.0289 1.0019 0.9981
0.750 -0.0471 0.03757 0.02820 -0.0304 1.0019 0.9981
1.000 -0.0235 0.03856 0.02905 -0.0319 1.0019 0.9981
1.250 -0.0005 0.03962 0.02999 -0.0332 1.0019 0.9981
1.500 0.0220 0.04076 0.03100 -0.0346 1.0019 0.9981
1.750 0.0438 0.04196 0.03212 -0.0359 1.0019 0.9981
2.000 0.0651 0.04324 0.03333 -0.0372 1.0019 0.9981
2.250 0.0856 0.04459 0.03463 -0.0385 1.0019 0.9981
2.500 0.1055 0.04603 0.03602 -0.0397 1.0019 0.9981
2.750 0.1576 0.04929 0.03919 -0.0469 0.9864 0.9981
3.000 0.2607 0.05256 0.04232 -0.0605 0.9156 0.9981
3.250 0.3094 0.05336 0.04306 -0.0647 0.8820 0.9981
3.500 0.3586 0.05427 0.04394 -0.0689 0.8590 0.9981
3.750 0.3903 0.05473 0.04440 -0.0705 0.8363 0.9981
4.000 0.4329 0.05523 0.04491 -0.0735 0.8164 0.9981
4.250 0.4810 0.05556 0.04526 -0.0770 0.7984 0.9981
4.500 0.5090 0.05584 0.04559 -0.0777 0.7774 0.9981
4.750 0.5457 0.05599 0.04578 -0.0794 0.7578 0.9981
5.000 0.5844 0.05594 0.04581 -0.0811 0.7391 0.9981
5.250 0.6226 0.05573 0.04566 -0.0824 0.7205 0.9981
5.500 0.6602 0.05538 0.04540 -0.0835 0.7021 0.9981
5.750 0.6967 0.05496 0.04507 -0.0843 0.6838 0.9981
6.000 0.7336 0.05439 0.04461 -0.0849 0.6656 0.9981
6.250 0.7707 0.05368 0.04402 -0.0853 0.6480 0.9981
6.500 0.8410 0.05008 0.04060 -0.0877 0.6392 0.9981
6.750 0.8748 0.04911 0.03974 -0.0872 0.6214 0.9981
7.000 0.9118 0.04794 0.03870 -0.0870 0.6040 0.9981
7.250 0.9575 0.04616 0.03707 -0.0875 0.5878 0.9981
7.500 1.0397 0.04186 0.03291 -0.0913 0.5741 0.9981
7.750 1.1092 0.03949 0.03065 -0.0951 0.5542 0.9981
8.000 1.1596 0.03896 0.03020 -0.0975 0.5331 0.9981
8.250 1.2049 0.03911 0.03041 -0.0997 0.5130 0.9981
8.500 1.2493 0.03960 0.03097 -0.1020 0.4944 0.9981
8.750 1.2980 0.04027 0.03169 -0.1051 0.4766 0.9981
9.000 1.2839 0.04275 0.03441 -0.0998 0.4651 0.9981
9.250 1.3135 0.04408 0.03586 -0.1003 0.4513 0.9981
9.500 1.3639 0.04490 0.03676 -0.1036 0.4357 0.9981
9.750 1.3313 0.04806 0.04021 -0.0961 0.4285 0.9981
10.000 1.3759 0.04888 0.04112 -0.0983 0.4139 0.9981
10.250 1.3370 0.05265 0.04515 -0.0906 0.4079 0.9981
10.500 1.3807 0.05321 0.04583 -0.0924 0.3930 0.9981
10.750 1.3254 0.05826 0.05112 -0.0839 0.3895 0.9981
11.000 1.2013 0.07075 0.06364 -0.0741 0.3916 0.9981
11.250 0.9752 0.10552 0.09790 -0.0781 0.3944 0.9981
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