SA7025 (sa7025-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7025 (sa7025-il) Reynolds number: 50,000 Max Cl/Cd: 41.88 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7025-il-50000-n5.txt Download as CSV file: xf-sa7025-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7025
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3595 0.10141 0.09485 -0.0315 1.0000 0.1054
-7.750 -0.3789 0.10095 0.09459 -0.0321 1.0000 0.1067
-7.500 -0.3900 0.09926 0.09307 -0.0337 1.0000 0.1071
-7.250 -0.3792 0.09468 0.08850 -0.0304 1.0000 0.1084
-7.000 -0.3776 0.09170 0.08558 -0.0291 1.0000 0.1094
-6.750 -0.3792 0.08902 0.08298 -0.0286 1.0000 0.1101
-6.500 -0.3814 0.08634 0.08038 -0.0286 1.0000 0.1105
-6.250 -0.3782 0.07783 0.07173 -0.0408 1.0000 0.0532
-6.000 -0.3752 0.07558 0.06954 -0.0354 1.0000 0.0504
-5.750 -0.3718 0.07226 0.06623 -0.0358 1.0000 0.0484
-5.500 -0.3660 0.06846 0.06242 -0.0374 1.0000 0.0465
-5.250 -0.3568 0.06416 0.05804 -0.0400 1.0000 0.0447
-5.000 -0.3438 0.05956 0.05330 -0.0430 1.0000 0.0435
-4.750 -0.3273 0.05493 0.04845 -0.0459 1.0000 0.0428
-4.500 -0.3098 0.05110 0.04440 -0.0479 1.0000 0.0432
-4.250 -0.2901 0.04744 0.04048 -0.0497 1.0000 0.0439
-4.000 -0.2668 0.04357 0.03620 -0.0517 1.0000 0.0438
-3.750 -0.2405 0.03972 0.03175 -0.0536 1.0000 0.0428
-3.500 -0.2129 0.03630 0.02771 -0.0549 1.0000 0.0421
-3.250 -0.1863 0.03365 0.02451 -0.0555 1.0000 0.0418
-3.000 -0.1581 0.03137 0.02177 -0.0561 0.9992 0.0422
-2.750 -0.1199 0.02929 0.01920 -0.0584 0.9943 0.0432
-2.500 -0.0832 0.02763 0.01716 -0.0601 0.9887 0.0447
-2.250 -0.0455 0.02629 0.01547 -0.0618 0.9832 0.0473
-2.000 -0.0104 0.02527 0.01406 -0.0630 0.9764 0.0509
-1.750 0.0286 0.02447 0.01305 -0.0653 0.9704 0.0629
-1.500 0.0650 0.02358 0.01212 -0.0671 0.9629 0.0875
-1.250 0.1011 0.02116 0.01179 -0.0697 0.9584 0.4792
-1.000 0.1314 0.01987 0.01139 -0.0688 0.9493 1.0000
-0.750 0.1710 0.02017 0.01110 -0.0712 0.9409 1.0000
-0.500 0.2069 0.02044 0.01095 -0.0730 0.9310 1.0000
-0.250 0.2409 0.02068 0.01086 -0.0744 0.9205 1.0000
0.000 0.2765 0.02092 0.01079 -0.0761 0.9103 1.0000
0.250 0.3164 0.02113 0.01074 -0.0785 0.9015 1.0000
0.500 0.3486 0.02132 0.01076 -0.0794 0.8897 1.0000
0.750 0.3813 0.02150 0.01078 -0.0803 0.8780 1.0000
1.000 0.4146 0.02165 0.01081 -0.0813 0.8664 1.0000
1.250 0.4478 0.02177 0.01083 -0.0822 0.8547 1.0000
1.500 0.4809 0.02185 0.01084 -0.0830 0.8430 1.0000
1.750 0.5141 0.02188 0.01084 -0.0837 0.8311 1.0000
2.000 0.5469 0.02188 0.01081 -0.0842 0.8189 1.0000
2.250 0.5780 0.02188 0.01080 -0.0843 0.8057 1.0000
2.500 0.6072 0.02190 0.01083 -0.0841 0.7912 1.0000
2.750 0.6357 0.02192 0.01092 -0.0838 0.7761 1.0000
3.000 0.6644 0.02192 0.01096 -0.0835 0.7606 1.0000
3.250 0.6935 0.02190 0.01098 -0.0831 0.7447 1.0000
3.500 0.7232 0.02184 0.01098 -0.0827 0.7284 1.0000
3.750 0.7538 0.02175 0.01101 -0.0824 0.7118 1.0000
4.000 0.7809 0.02179 0.01113 -0.0817 0.6925 1.0000
4.250 0.8092 0.02181 0.01121 -0.0810 0.6728 1.0000
4.500 0.8367 0.02188 0.01134 -0.0802 0.6521 1.0000
4.750 0.8639 0.02200 0.01152 -0.0794 0.6303 1.0000
5.000 0.8892 0.02221 0.01190 -0.0784 0.6068 1.0000
5.250 0.9147 0.02245 0.01220 -0.0774 0.5826 1.0000
5.500 0.9395 0.02275 0.01254 -0.0763 0.5576 1.0000
5.750 0.9633 0.02311 0.01296 -0.0751 0.5315 1.0000
6.000 0.9859 0.02355 0.01347 -0.0738 0.5046 1.0000
6.250 1.0077 0.02406 0.01404 -0.0724 0.4770 1.0000
6.500 1.0285 0.02464 0.01477 -0.0710 0.4487 1.0000
6.750 1.0482 0.02528 0.01549 -0.0694 0.4195 1.0000
7.000 1.0669 0.02599 0.01628 -0.0678 0.3898 1.0000
7.250 1.0847 0.02677 0.01714 -0.0661 0.3600 1.0000
7.500 1.1014 0.02764 0.01807 -0.0643 0.3302 1.0000
7.750 1.1166 0.02860 0.01907 -0.0624 0.3001 1.0000
8.000 1.1300 0.02967 0.02024 -0.0604 0.2694 1.0000
8.250 1.1415 0.03086 0.02150 -0.0582 0.2373 1.0000
8.500 1.1506 0.03220 0.02285 -0.0560 0.2060 1.0000
8.750 1.1569 0.03376 0.02436 -0.0535 0.1742 1.0000
9.000 1.1602 0.03555 0.02611 -0.0509 0.1414 1.0000
9.250 1.1593 0.03773 0.02815 -0.0480 0.1117 1.0000
9.500 1.1558 0.04027 0.03048 -0.0455 0.0845 1.0000
10.000 1.1521 0.04575 0.03587 -0.0416 0.0501 1.0000
10.250 1.1511 0.04872 0.03897 -0.0398 0.0431 1.0000
10.500 1.1492 0.05173 0.04205 -0.0385 0.0384 1.0000
10.750 1.1493 0.05484 0.04535 -0.0373 0.0350 1.0000
11.000 1.1509 0.05793 0.04872 -0.0363 0.0315 1.0000
11.250 1.1502 0.06124 0.05221 -0.0356 0.0293 1.0000
11.500 1.1485 0.06475 0.05587 -0.0353 0.0278 1.0000
11.750 1.1474 0.06857 0.05984 -0.0349 0.0268 1.0000
12.000 1.1473 0.07260 0.06425 -0.0347 0.0261 1.0000
12.250 1.1440 0.07707 0.06905 -0.0351 0.0257 1.0000
12.500 1.1367 0.08212 0.07443 -0.0362 0.0254 1.0000
12.750 1.1267 0.08772 0.08031 -0.0380 0.0252 1.0000
13.000 1.1145 0.09391 0.08676 -0.0407 0.0252 1.0000
13.250 1.1009 0.10062 0.09370 -0.0440 0.0253 1.0000
13.500 1.0864 0.10797 0.10125 -0.0481 0.0254 1.0000
13.750 1.0717 0.11587 0.10934 -0.0527 0.0255 1.0000
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