S9000 (9%) (s9000-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 100,000 Max Cl/Cd: 53.26 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9000-il-100000.txt Download as CSV file: xf-s9000-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S9000 (9%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4213 0.09626 0.09138 -0.0262 1.0000 0.0917
-8.250 -0.4442 0.09401 0.08928 -0.0313 1.0000 0.0937
-8.000 -0.4673 0.09069 0.08610 -0.0380 1.0000 0.0941
-7.750 -0.4232 0.08653 0.08185 -0.0272 1.0000 0.0999
-7.500 -0.4280 0.08378 0.07919 -0.0273 1.0000 0.1027
-7.250 -0.4456 0.08026 0.07580 -0.0326 1.0000 0.1066
-7.000 -0.4649 0.07544 0.07091 -0.0411 1.0000 0.1084
-6.750 -0.4416 0.07336 0.06901 -0.0319 1.0000 0.1132
-6.500 -0.4552 0.06924 0.06471 -0.0402 1.0000 0.1216
-6.250 -0.4445 0.06582 0.06149 -0.0356 1.0000 0.1253
-6.000 -0.4482 0.06220 0.05761 -0.0403 1.0000 0.1367
-5.750 -0.4357 0.05968 0.05534 -0.0351 1.0000 0.1415
-5.500 -0.4314 0.05616 0.05173 -0.0363 1.0000 0.1533
-5.250 -0.4239 0.05307 0.04852 -0.0369 1.0000 0.1664
-5.000 -0.3930 0.03873 0.03290 -0.0439 1.0000 0.0740
-4.750 -0.3659 0.03258 0.02542 -0.0436 1.0000 0.0535
-4.500 -0.3446 0.02887 0.02137 -0.0432 1.0000 0.0518
-4.250 -0.3206 0.02607 0.01809 -0.0426 1.0000 0.0513
-4.000 -0.2957 0.02387 0.01544 -0.0417 1.0000 0.0522
-3.750 -0.2716 0.02194 0.01330 -0.0412 1.0000 0.0584
-3.500 -0.2467 0.02063 0.01177 -0.0403 1.0000 0.0657
-3.250 -0.2222 0.01934 0.01041 -0.0396 1.0000 0.0805
-3.000 -0.1980 0.01790 0.00916 -0.0391 1.0000 0.1069
-2.750 -0.1738 0.01658 0.00822 -0.0387 1.0000 0.1591
-2.500 -0.1494 0.01474 0.00764 -0.0389 1.0000 0.3741
-2.250 -0.1332 0.01384 0.00778 -0.0366 1.0000 0.6085
-2.000 -0.1252 0.01368 0.00810 -0.0317 1.0000 0.7732
-1.750 -0.1195 0.01362 0.00822 -0.0262 1.0000 0.8930
-1.500 -0.0881 0.01351 0.00792 -0.0278 1.0000 1.0000
-1.250 -0.0497 0.01393 0.00800 -0.0310 0.9949 1.0000
-1.000 0.0014 0.01440 0.00816 -0.0363 0.9846 1.0000
-0.750 0.0501 0.01475 0.00827 -0.0410 0.9733 1.0000
-0.500 0.0970 0.01502 0.00833 -0.0452 0.9616 1.0000
-0.250 0.1431 0.01522 0.00837 -0.0491 0.9496 1.0000
0.000 0.1892 0.01534 0.00836 -0.0529 0.9377 1.0000
0.250 0.2368 0.01537 0.00829 -0.0568 0.9260 1.0000
0.500 0.2886 0.01527 0.00812 -0.0612 0.9156 1.0000
0.750 0.3341 0.01511 0.00791 -0.0643 0.9028 1.0000
1.000 0.3782 0.01491 0.00769 -0.0670 0.8898 1.0000
1.250 0.4204 0.01468 0.00745 -0.0691 0.8762 1.0000
1.500 0.4609 0.01442 0.00718 -0.0708 0.8615 1.0000
1.750 0.4992 0.01416 0.00691 -0.0719 0.8456 1.0000
2.000 0.5319 0.01400 0.00674 -0.0719 0.8267 1.0000
2.250 0.5624 0.01390 0.00664 -0.0716 0.8062 1.0000
2.500 0.5933 0.01381 0.00650 -0.0713 0.7862 1.0000
2.750 0.6197 0.01385 0.00651 -0.0703 0.7623 1.0000
3.000 0.6463 0.01390 0.00650 -0.0693 0.7378 1.0000
3.250 0.6728 0.01397 0.00654 -0.0683 0.7125 1.0000
3.500 0.6986 0.01409 0.00658 -0.0672 0.6862 1.0000
3.750 0.7235 0.01427 0.00669 -0.0661 0.6584 1.0000
4.000 0.7481 0.01449 0.00687 -0.0649 0.6299 1.0000
4.250 0.7724 0.01476 0.00705 -0.0638 0.6007 1.0000
4.500 0.7960 0.01508 0.00730 -0.0626 0.5698 1.0000
4.750 0.8192 0.01543 0.00758 -0.0614 0.5378 1.0000
5.000 0.8421 0.01581 0.00790 -0.0602 0.5053 1.0000
5.250 0.8648 0.01626 0.00823 -0.0590 0.4732 1.0000
5.500 0.8870 0.01675 0.00864 -0.0578 0.4405 1.0000
5.750 0.9089 0.01729 0.00911 -0.0566 0.4077 1.0000
6.000 0.9306 0.01790 0.00964 -0.0554 0.3760 1.0000
6.250 0.9519 0.01857 0.01020 -0.0542 0.3450 1.0000
6.500 0.9728 0.01930 0.01082 -0.0530 0.3147 1.0000
6.750 0.9930 0.02005 0.01152 -0.0518 0.2842 1.0000
7.000 1.0130 0.02089 0.01229 -0.0506 0.2555 1.0000
7.250 1.0327 0.02183 0.01317 -0.0494 0.2288 1.0000
7.500 1.0520 0.02283 0.01410 -0.0482 0.2035 1.0000
7.750 1.0715 0.02397 0.01526 -0.0469 0.1805 1.0000
8.000 1.0916 0.02531 0.01647 -0.0459 0.1615 1.0000
8.250 1.1106 0.02663 0.01788 -0.0446 0.1433 1.0000
8.500 1.1303 0.02811 0.01942 -0.0435 0.1280 1.0000
8.750 1.1492 0.02962 0.02103 -0.0423 0.1146 1.0000
9.000 1.1680 0.03127 0.02274 -0.0412 0.1028 1.0000
9.250 1.1859 0.03299 0.02450 -0.0400 0.0919 1.0000
9.500 1.2042 0.03495 0.02645 -0.0390 0.0819 1.0000
9.750 1.2169 0.03684 0.02876 -0.0370 0.0736 1.0000
10.000 1.2325 0.03972 0.03177 -0.0358 0.0669 1.0000
10.250 1.2425 0.04170 0.03408 -0.0337 0.0607 1.0000
10.500 1.2555 0.04552 0.03798 -0.0327 0.0564 1.0000
10.750 1.2552 0.04871 0.04182 -0.0296 0.0544 1.0000
11.000 1.2520 0.05195 0.04551 -0.0268 0.0520 1.0000
11.250 1.2547 0.05422 0.04794 -0.0248 0.0488 1.0000
11.500 1.2570 0.05779 0.05153 -0.0235 0.0463 1.0000
11.750 1.2421 0.06244 0.05648 -0.0209 0.0458 1.0000
12.000 1.2230 0.06630 0.06061 -0.0185 0.0457 1.0000
12.250 1.2025 0.07039 0.06497 -0.0171 0.0456 1.0000
12.500 1.1816 0.07516 0.06997 -0.0171 0.0457 1.0000
12.750 1.1602 0.07992 0.07499 -0.0182 0.0459 1.0000
13.000 1.1345 0.08542 0.08075 -0.0211 0.0464 1.0000
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Polar data table (+)
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