S9000 (9%) (s9000-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 200,000 Max Cl/Cd: 71.01 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9000-il-200000.txt Download as CSV file: xf-s9000-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4413 0.08552 0.08216 -0.0375 1.0000 0.0417
-8.000 -0.4502 0.08079 0.07746 -0.0419 1.0000 0.0418
-7.750 -0.4593 0.07483 0.07158 -0.0418 1.0000 0.0426
-7.500 -0.4553 0.07276 0.06956 -0.0386 1.0000 0.0434
-7.250 -0.4533 0.07016 0.06700 -0.0377 1.0000 0.0444
-7.000 -0.4529 0.06691 0.06374 -0.0383 1.0000 0.0453
-6.750 -0.4528 0.06332 0.06013 -0.0393 1.0000 0.0464
-6.500 -0.4522 0.05946 0.05622 -0.0403 1.0000 0.0479
-6.250 -0.4500 0.05540 0.05205 -0.0413 1.0000 0.0499
-6.000 -0.4451 0.05260 0.04852 -0.0435 1.0000 0.0540
-5.750 -0.4296 0.03439 0.03092 -0.0394 1.0000 0.0560
-5.500 -0.4222 0.03190 0.02844 -0.0382 1.0000 0.0574
-5.250 -0.4133 0.02935 0.02579 -0.0375 1.0000 0.0595
-5.000 -0.3953 0.02967 0.02436 -0.0416 1.0000 0.0288
-4.750 -0.3704 0.02446 0.01814 -0.0409 1.0000 0.0227
-4.500 -0.3480 0.02312 0.01650 -0.0399 1.0000 0.0223
-4.250 -0.3238 0.02097 0.01401 -0.0394 1.0000 0.0222
-4.000 -0.2948 0.01834 0.01108 -0.0397 0.9993 0.0230
-3.750 -0.2548 0.01720 0.00990 -0.0425 0.9953 0.0278
-3.500 -0.2161 0.01575 0.00832 -0.0445 0.9911 0.0329
-3.250 -0.1761 0.01460 0.00721 -0.0471 0.9865 0.0490
-3.000 -0.1354 0.01357 0.00631 -0.0498 0.9821 0.0930
-2.750 -0.0982 0.01230 0.00577 -0.0525 0.9760 0.2376
-2.500 -0.0571 0.01148 0.00560 -0.0558 0.9712 0.4121
-2.250 -0.0239 0.01077 0.00552 -0.0570 0.9631 0.5766
-2.000 0.0128 0.01035 0.00559 -0.0581 0.9575 0.7294
-1.750 0.0420 0.01015 0.00551 -0.0574 0.9478 0.8048
-1.500 0.0747 0.00998 0.00540 -0.0574 0.9409 0.8610
-1.250 0.1053 0.00980 0.00522 -0.0568 0.9327 0.9063
-1.000 0.1481 0.00961 0.00496 -0.0589 0.9281 0.9460
-0.750 0.2008 0.00942 0.00468 -0.0635 0.9216 0.9754
-0.500 0.2617 0.00917 0.00432 -0.0698 0.9172 0.9941
-0.250 0.3029 0.00895 0.00403 -0.0725 0.9058 1.0000
0.000 0.3354 0.00877 0.00377 -0.0733 0.8920 1.0000
0.250 0.3655 0.00864 0.00355 -0.0735 0.8765 1.0000
0.500 0.3940 0.00856 0.00337 -0.0734 0.8598 1.0000
0.750 0.4198 0.00855 0.00327 -0.0727 0.8408 1.0000
1.000 0.4454 0.00857 0.00320 -0.0720 0.8208 1.0000
1.250 0.4719 0.00862 0.00313 -0.0714 0.8016 1.0000
1.500 0.4971 0.00871 0.00313 -0.0707 0.7803 1.0000
1.750 0.5231 0.00881 0.00312 -0.0701 0.7597 1.0000
2.000 0.5484 0.00892 0.00317 -0.0693 0.7369 1.0000
2.250 0.5740 0.00906 0.00319 -0.0686 0.7137 1.0000
2.500 0.5992 0.00922 0.00324 -0.0679 0.6888 1.0000
2.750 0.6244 0.00939 0.00332 -0.0672 0.6635 1.0000
3.000 0.6496 0.00959 0.00344 -0.0665 0.6385 1.0000
3.250 0.6746 0.00981 0.00355 -0.0658 0.6129 1.0000
3.500 0.6995 0.01005 0.00369 -0.0650 0.5866 1.0000
3.750 0.7241 0.01031 0.00386 -0.0643 0.5589 1.0000
4.000 0.7486 0.01059 0.00406 -0.0636 0.5302 1.0000
4.250 0.7726 0.01089 0.00426 -0.0628 0.5000 1.0000
4.500 0.7967 0.01122 0.00449 -0.0620 0.4698 1.0000
4.750 0.8206 0.01157 0.00475 -0.0613 0.4404 1.0000
5.000 0.8444 0.01194 0.00506 -0.0606 0.4107 1.0000
5.250 0.8680 0.01235 0.00538 -0.0598 0.3811 1.0000
5.500 0.8914 0.01279 0.00573 -0.0591 0.3521 1.0000
5.750 0.9144 0.01325 0.00611 -0.0583 0.3219 1.0000
6.000 0.9372 0.01375 0.00653 -0.0575 0.2922 1.0000
6.250 0.9598 0.01428 0.00698 -0.0568 0.2638 1.0000
6.500 0.9823 0.01483 0.00747 -0.0560 0.2372 1.0000
6.750 1.0044 0.01544 0.00800 -0.0552 0.2127 1.0000
7.000 1.0261 0.01611 0.00862 -0.0543 0.1897 1.0000
7.250 1.0478 0.01678 0.00928 -0.0535 0.1672 1.0000
7.500 1.0679 0.01761 0.01000 -0.0524 0.1468 1.0000
7.750 1.0888 0.01838 0.01079 -0.0515 0.1273 1.0000
8.000 1.1084 0.01926 0.01164 -0.0503 0.1110 1.0000
8.250 1.1276 0.02018 0.01253 -0.0492 0.0967 1.0000
8.500 1.1466 0.02112 0.01352 -0.0480 0.0849 1.0000
8.750 1.1648 0.02215 0.01460 -0.0467 0.0751 1.0000
9.000 1.1815 0.02332 0.01580 -0.0453 0.0665 1.0000
9.250 1.1980 0.02440 0.01690 -0.0439 0.0583 1.0000
9.500 1.2146 0.02550 0.01815 -0.0424 0.0507 1.0000
9.750 1.2264 0.02733 0.01999 -0.0405 0.0448 1.0000
10.000 1.2413 0.02849 0.02133 -0.0388 0.0395 1.0000
10.250 1.2508 0.03085 0.02367 -0.0369 0.0350 1.0000
10.500 1.2633 0.03219 0.02531 -0.0348 0.0322 1.0000
10.750 1.2729 0.03383 0.02710 -0.0326 0.0297 1.0000
11.000 1.2796 0.03569 0.02902 -0.0305 0.0274 1.0000
11.250 1.2830 0.03872 0.03229 -0.0282 0.0254 1.0000
11.500 1.2859 0.04055 0.03440 -0.0257 0.0239 1.0000
11.750 1.2869 0.04288 0.03696 -0.0235 0.0227 1.0000
12.000 1.2857 0.04497 0.03922 -0.0216 0.0213 1.0000
12.250 1.2851 0.04690 0.04119 -0.0203 0.0200 1.0000
12.500 1.2766 0.05098 0.04543 -0.0192 0.0189 1.0000
12.750 1.2621 0.05547 0.05022 -0.0185 0.0185 1.0000
13.000 1.2512 0.05916 0.05419 -0.0186 0.0181 1.0000
13.250 1.2379 0.06383 0.05913 -0.0194 0.0179 1.0000
13.500 1.2225 0.06912 0.06466 -0.0212 0.0177 1.0000
13.750 1.2052 0.07518 0.07097 -0.0239 0.0176 1.0000
14.000 1.1870 0.08186 0.07786 -0.0274 0.0177 1.0000
14.250 1.1670 0.08938 0.08560 -0.0319 0.0177 1.0000
14.500 1.1468 0.09747 0.09387 -0.0369 0.0179 1.0000
14.750 1.1252 0.10650 0.10307 -0.0427 0.0181 1.0000
15.000 1.1033 0.11615 0.11285 -0.0489 0.0184 1.0000
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Polar data table (+)
Polar graphs
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