AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AIRFOIL 3024 9.84% (s3024-il) Reynolds number: 50,000 Max Cl/Cd: 38.27 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3024-il-50000-n5.txt Download as CSV file: xf-s3024-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AIRFOIL 3024 9.84%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3482 0.10787 0.10115 -0.0379 1.0000 0.1146
-8.750 -0.3598 0.10615 0.09959 -0.0395 1.0000 0.1152
-8.500 -0.3712 0.10425 0.09783 -0.0399 1.0000 0.1154
-8.000 -0.3584 0.09193 0.08548 -0.0397 1.0000 0.0582
-7.750 -0.3665 0.08972 0.08339 -0.0378 1.0000 0.0565
-7.500 -0.3804 0.08792 0.08170 -0.0357 1.0000 0.0552
-7.250 -0.3942 0.08553 0.07942 -0.0346 1.0000 0.0537
-6.750 -0.4244 0.07723 0.07117 -0.0390 1.0000 0.0479
-6.500 -0.4270 0.07451 0.06848 -0.0376 1.0000 0.0473
-6.250 -0.4290 0.07150 0.06547 -0.0370 1.0000 0.0466
-6.000 -0.4293 0.06823 0.06216 -0.0368 1.0000 0.0459
-5.750 -0.4174 0.06375 0.05753 -0.0396 0.9966 0.0450
-5.500 -0.3948 0.05824 0.05174 -0.0447 0.9900 0.0439
-5.250 -0.3695 0.05289 0.04601 -0.0494 0.9840 0.0430
-5.000 -0.3442 0.04799 0.04062 -0.0528 0.9776 0.0423
-4.750 -0.3147 0.04362 0.03568 -0.0559 0.9724 0.0420
-4.500 -0.2878 0.04031 0.03183 -0.0576 0.9662 0.0431
-4.250 -0.2552 0.03728 0.02817 -0.0597 0.9612 0.0452
-4.000 -0.2256 0.03482 0.02503 -0.0605 0.9555 0.0471
-3.750 -0.1936 0.03262 0.02229 -0.0614 0.9502 0.0486
-3.500 -0.1587 0.03081 0.02025 -0.0631 0.9460 0.0511
-3.250 -0.1321 0.02956 0.01878 -0.0629 0.9392 0.0547
-3.000 -0.0980 0.02839 0.01732 -0.0639 0.9341 0.0621
-2.750 -0.0660 0.02741 0.01612 -0.0646 0.9284 0.0730
-2.500 -0.0355 0.02649 0.01524 -0.0653 0.9220 0.0963
-2.250 0.0014 0.02528 0.01443 -0.0675 0.9175 0.1776
-2.000 0.0259 0.02420 0.01401 -0.0675 0.9100 0.3158
-1.750 0.0519 0.02297 0.01391 -0.0670 0.9045 0.5664
-1.500 0.1176 0.02215 0.01359 -0.0724 0.9027 1.0000
-1.250 0.1416 0.02238 0.01340 -0.0720 0.8932 1.0000
-1.000 0.1810 0.02257 0.01320 -0.0744 0.8875 1.0000
-0.750 0.2034 0.02283 0.01316 -0.0737 0.8774 1.0000
-0.500 0.2381 0.02303 0.01308 -0.0751 0.8707 1.0000
-0.250 0.2637 0.02328 0.01310 -0.0748 0.8611 1.0000
0.000 0.2919 0.02352 0.01314 -0.0750 0.8525 1.0000
0.250 0.3234 0.02370 0.01313 -0.0757 0.8444 1.0000
0.500 0.3477 0.02397 0.01326 -0.0752 0.8343 1.0000
0.750 0.3835 0.02406 0.01321 -0.0764 0.8276 1.0000
1.000 0.4053 0.02435 0.01339 -0.0755 0.8162 1.0000
1.250 0.4316 0.02456 0.01351 -0.0751 0.8063 1.0000
1.500 0.4647 0.02461 0.01349 -0.0758 0.7984 1.0000
1.750 0.4873 0.02487 0.01369 -0.0748 0.7867 1.0000
2.000 0.5131 0.02504 0.01383 -0.0743 0.7761 1.0000
2.250 0.5473 0.02496 0.01371 -0.0748 0.7681 1.0000
2.500 0.5699 0.02517 0.01393 -0.0738 0.7556 1.0000
2.750 0.5943 0.02532 0.01408 -0.0729 0.7435 1.0000
3.000 0.6206 0.02539 0.01416 -0.0723 0.7319 1.0000
3.250 0.6514 0.02527 0.01406 -0.0721 0.7219 1.0000
3.500 0.6784 0.02525 0.01411 -0.0714 0.7098 1.0000
3.750 0.7028 0.02533 0.01423 -0.0705 0.6964 1.0000
4.000 0.7279 0.02537 0.01433 -0.0695 0.6827 1.0000
4.250 0.7533 0.02538 0.01444 -0.0686 0.6688 1.0000
4.500 0.7791 0.02537 0.01449 -0.0676 0.6544 1.0000
4.750 0.8051 0.02534 0.01454 -0.0667 0.6394 1.0000
5.000 0.8314 0.02529 0.01457 -0.0657 0.6238 1.0000
5.250 0.8581 0.02522 0.01461 -0.0648 0.6074 1.0000
5.500 0.8835 0.02523 0.01469 -0.0637 0.5897 1.0000
5.750 0.9059 0.02540 0.01495 -0.0624 0.5697 1.0000
6.000 0.9311 0.02546 0.01511 -0.0613 0.5498 1.0000
6.250 0.9546 0.02563 0.01534 -0.0600 0.5285 1.0000
6.500 0.9769 0.02590 0.01566 -0.0587 0.5059 1.0000
6.750 0.9984 0.02625 0.01606 -0.0573 0.4828 1.0000
7.000 1.0195 0.02664 0.01650 -0.0558 0.4592 1.0000
7.250 1.0379 0.02720 0.01713 -0.0542 0.4348 1.0000
7.500 1.0567 0.02778 0.01771 -0.0526 0.4111 1.0000
7.750 1.0735 0.02847 0.01844 -0.0508 0.3869 1.0000
8.000 1.0894 0.02926 0.01929 -0.0491 0.3634 1.0000
8.250 1.1049 0.03008 0.02012 -0.0473 0.3409 1.0000
8.500 1.1182 0.03104 0.02115 -0.0453 0.3183 1.0000
8.750 1.1314 0.03203 0.02215 -0.0434 0.2974 1.0000
9.000 1.1427 0.03313 0.02332 -0.0414 0.2768 1.0000
9.250 1.1522 0.03428 0.02457 -0.0392 0.2574 1.0000
9.500 1.1610 0.03551 0.02581 -0.0370 0.2393 1.0000
9.750 1.1683 0.03687 0.02723 -0.0348 0.2215 1.0000
10.000 1.1745 0.03835 0.02883 -0.0327 0.2042 1.0000
10.250 1.1789 0.03996 0.03052 -0.0306 0.1875 1.0000
10.500 1.1821 0.04172 0.03234 -0.0287 0.1716 1.0000
10.750 1.1824 0.04369 0.03434 -0.0268 0.1560 1.0000
11.000 1.1793 0.04592 0.03661 -0.0251 0.1407 1.0000
11.250 1.1733 0.04853 0.03927 -0.0239 0.1241 1.0000
11.500 1.1677 0.05138 0.04218 -0.0230 0.1087 1.0000
11.750 1.1612 0.05458 0.04541 -0.0225 0.0941 1.0000
12.000 1.1558 0.05798 0.04885 -0.0222 0.0828 1.0000
12.250 1.1501 0.06159 0.05247 -0.0221 0.0744 1.0000
12.500 1.1440 0.06547 0.05643 -0.0222 0.0663 1.0000
12.750 1.1395 0.06937 0.06047 -0.0224 0.0602 1.0000
13.000 1.1340 0.07341 0.06457 -0.0228 0.0556 1.0000
13.250 1.1307 0.07740 0.06868 -0.0232 0.0523 1.0000
13.500 1.1279 0.08159 0.07312 -0.0236 0.0490 1.0000
13.750 1.1247 0.08577 0.07744 -0.0244 0.0468 1.0000
14.000 1.1218 0.08986 0.08158 -0.0253 0.0449 1.0000
14.250 1.1170 0.09470 0.08663 -0.0266 0.0434 1.0000
14.500 1.1088 0.10044 0.09270 -0.0286 0.0423 1.0000
14.750 1.0979 0.10687 0.09940 -0.0315 0.0414 1.0000
15.000 1.0850 0.11400 0.10676 -0.0349 0.0410 1.0000
15.250 1.0692 0.12220 0.11519 -0.0393 0.0409 1.0000
15.500 1.0499 0.13183 0.12502 -0.0447 0.0413 1.0000
15.750 1.0269 0.14330 0.13663 -0.0515 0.0420 1.0000
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Polar data table (+)
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