S9000 (9%) (s9000-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 100,000 Max Cl/Cd: 52.69 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9000-il-100000-n5.txt Download as CSV file: xf-s9000-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4305 0.08982 0.08478 -0.0287 1.0000 0.0189
-8.500 -0.4329 0.08579 0.08082 -0.0302 1.0000 0.0185
-8.250 -0.4376 0.08158 0.07670 -0.0317 1.0000 0.0180
-8.000 -0.4458 0.07723 0.07245 -0.0333 1.0000 0.0177
-7.750 -0.4583 0.07226 0.06758 -0.0358 1.0000 0.0171
-7.500 -0.4717 0.06111 0.05632 -0.0444 1.0000 0.0157
-7.250 -0.4760 0.05648 0.05161 -0.0457 1.0000 0.0156
-7.000 -0.4771 0.05222 0.04721 -0.0465 1.0000 0.0155
-6.750 -0.4755 0.04791 0.04268 -0.0469 1.0000 0.0154
-6.500 -0.4709 0.04348 0.03794 -0.0470 1.0000 0.0153
-6.250 -0.4621 0.03940 0.03346 -0.0468 1.0000 0.0153
-6.000 -0.4493 0.03548 0.02896 -0.0464 1.0000 0.0157
-5.750 -0.4348 0.03273 0.02596 -0.0459 1.0000 0.0165
-5.500 -0.4174 0.03122 0.02429 -0.0453 1.0000 0.0180
-5.250 -0.3981 0.02887 0.02153 -0.0446 1.0000 0.0190
-5.000 -0.3769 0.02646 0.01862 -0.0438 1.0000 0.0200
-4.750 -0.3547 0.02440 0.01616 -0.0429 1.0000 0.0207
-4.500 -0.3318 0.02267 0.01407 -0.0420 1.0000 0.0218
-4.250 -0.3094 0.02103 0.01230 -0.0413 1.0000 0.0235
-4.000 -0.2741 0.02003 0.01119 -0.0431 0.9955 0.0289
-3.750 -0.2388 0.01875 0.00981 -0.0449 0.9904 0.0359
-3.500 -0.2019 0.01776 0.00874 -0.0469 0.9849 0.0496
-3.250 -0.1667 0.01682 0.00784 -0.0487 0.9785 0.0744
-3.000 -0.1301 0.01589 0.00716 -0.0508 0.9722 0.1300
-2.750 -0.0966 0.01507 0.00675 -0.0525 0.9646 0.2313
-2.500 -0.0610 0.01433 0.00650 -0.0545 0.9580 0.3651
-2.250 -0.0305 0.01369 0.00634 -0.0552 0.9491 0.4978
-2.000 0.0009 0.01320 0.00634 -0.0553 0.9421 0.6413
-1.750 0.0288 0.01297 0.00628 -0.0544 0.9325 0.7438
-1.500 0.0570 0.01282 0.00617 -0.0535 0.9228 0.8117
-1.250 0.0902 0.01265 0.00598 -0.0535 0.9152 0.8664
-0.750 0.1714 0.01233 0.00548 -0.0574 0.8960 0.9608
-0.500 0.2226 0.01214 0.00516 -0.0620 0.8875 1.0000
-0.250 0.2553 0.01208 0.00495 -0.0629 0.8740 1.0000
0.000 0.2880 0.01202 0.00477 -0.0638 0.8599 1.0000
0.250 0.3206 0.01197 0.00461 -0.0646 0.8448 1.0000
0.500 0.3515 0.01195 0.00448 -0.0650 0.8282 1.0000
0.750 0.3811 0.01196 0.00439 -0.0651 0.8102 1.0000
1.000 0.4106 0.01199 0.00433 -0.0652 0.7921 1.0000
1.250 0.4401 0.01203 0.00428 -0.0652 0.7736 1.0000
1.500 0.4677 0.01211 0.00428 -0.0650 0.7530 1.0000
1.750 0.4955 0.01220 0.00428 -0.0647 0.7318 1.0000
2.000 0.5223 0.01232 0.00431 -0.0642 0.7094 1.0000
2.250 0.5493 0.01245 0.00437 -0.0638 0.6871 1.0000
2.500 0.5753 0.01262 0.00446 -0.0632 0.6635 1.0000
2.750 0.6014 0.01280 0.00456 -0.0626 0.6398 1.0000
3.000 0.6271 0.01301 0.00468 -0.0620 0.6153 1.0000
3.250 0.6524 0.01325 0.00486 -0.0614 0.5888 1.0000
3.500 0.6774 0.01351 0.00504 -0.0607 0.5619 1.0000
3.750 0.7021 0.01379 0.00525 -0.0599 0.5347 1.0000
4.000 0.7268 0.01410 0.00551 -0.0592 0.5081 1.0000
4.250 0.7511 0.01443 0.00578 -0.0585 0.4816 1.0000
4.500 0.7753 0.01479 0.00607 -0.0578 0.4548 1.0000
4.750 0.7991 0.01518 0.00640 -0.0570 0.4270 1.0000
5.000 0.8225 0.01561 0.00678 -0.0562 0.3988 1.0000
5.250 0.8457 0.01606 0.00717 -0.0554 0.3704 1.0000
5.500 0.8686 0.01655 0.00760 -0.0546 0.3428 1.0000
5.750 0.8915 0.01706 0.00807 -0.0539 0.3161 1.0000
6.000 0.9142 0.01759 0.00861 -0.0531 0.2906 1.0000
6.250 0.9365 0.01817 0.00917 -0.0523 0.2657 1.0000
6.500 0.9584 0.01880 0.00976 -0.0514 0.2419 1.0000
6.750 0.9798 0.01946 0.01039 -0.0506 0.2176 1.0000
7.000 1.0012 0.02015 0.01108 -0.0497 0.1948 1.0000
7.250 1.0217 0.02092 0.01185 -0.0488 0.1739 1.0000
7.500 1.0425 0.02168 0.01265 -0.0479 0.1543 1.0000
7.750 1.0622 0.02254 0.01352 -0.0469 0.1367 1.0000
8.000 1.0815 0.02345 0.01447 -0.0458 0.1225 1.0000
8.250 1.1001 0.02442 0.01550 -0.0446 0.1093 1.0000
8.500 1.1180 0.02545 0.01659 -0.0434 0.0968 1.0000
8.750 1.1352 0.02654 0.01780 -0.0422 0.0861 1.0000
9.000 1.1510 0.02774 0.01907 -0.0407 0.0770 1.0000
9.250 1.1648 0.02903 0.02036 -0.0392 0.0687 1.0000
9.500 1.1805 0.03020 0.02175 -0.0378 0.0607 1.0000
9.750 1.1923 0.03165 0.02329 -0.0361 0.0546 1.0000
10.000 1.2043 0.03300 0.02480 -0.0344 0.0485 1.0000
10.250 1.2117 0.03463 0.02652 -0.0322 0.0440 1.0000
10.500 1.2195 0.03625 0.02836 -0.0301 0.0398 1.0000
10.750 1.2234 0.03797 0.03021 -0.0279 0.0365 1.0000
11.000 1.2265 0.04004 0.03245 -0.0258 0.0335 1.0000
11.250 1.2299 0.04219 0.03484 -0.0239 0.0309 1.0000
11.500 1.2310 0.04452 0.03736 -0.0222 0.0291 1.0000
11.750 1.2299 0.04699 0.03996 -0.0209 0.0276 1.0000
12.000 1.2257 0.05006 0.04311 -0.0199 0.0262 1.0000
12.250 1.2224 0.05325 0.04662 -0.0193 0.0249 1.0000
12.500 1.2169 0.05682 0.05048 -0.0191 0.0236 1.0000
12.750 1.2094 0.06078 0.05471 -0.0196 0.0227 1.0000
13.000 1.2000 0.06526 0.05942 -0.0206 0.0220 1.0000
13.250 1.1888 0.07028 0.06466 -0.0224 0.0215 1.0000
13.500 1.1759 0.07588 0.07049 -0.0248 0.0212 1.0000
13.750 1.1608 0.08220 0.07702 -0.0280 0.0210 1.0000
14.000 1.1434 0.08940 0.08445 -0.0321 0.0210 1.0000
14.250 1.1224 0.09786 0.09312 -0.0372 0.0211 1.0000
14.500 1.0973 0.10798 0.10346 -0.0436 0.0215 1.0000
14.750 1.0674 0.12018 0.11584 -0.0514 0.0223 1.0000
15.000 1.0325 0.13486 0.13063 -0.0604 0.0238 1.0000
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Polar data table (+)
Polar graphs
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