AH 93-W-145 (ah93w145-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-145 (ah93w145-il) Reynolds number: 200,000 Max Cl/Cd: 80.28 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w145-il-200000-n5.txt Download as CSV file: xf-ah93w145-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-145
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6004 0.05412 0.05040 -0.0728 1.0000 0.0211
-11.000 -0.6445 0.04644 0.04246 -0.0773 1.0000 0.0209
-10.750 -0.6605 0.04072 0.03632 -0.0807 0.9552 0.0211
-10.500 -0.6440 0.03512 0.02998 -0.0868 0.8929 0.0219
-10.250 -0.6268 0.03173 0.02586 -0.0889 0.8485 0.0228
-10.000 -0.6059 0.03055 0.02450 -0.0892 0.8176 0.0234
-9.750 -0.5860 0.02954 0.02329 -0.0890 0.7940 0.0241
-9.500 -0.5668 0.02831 0.02177 -0.0887 0.7749 0.0249
-9.250 -0.5476 0.02690 0.02003 -0.0883 0.7585 0.0257
-9.000 -0.5273 0.02549 0.01828 -0.0879 0.7441 0.0266
-8.750 -0.5057 0.02424 0.01667 -0.0874 0.7315 0.0276
-8.500 -0.4832 0.02339 0.01573 -0.0872 0.7205 0.0287
-8.250 -0.4593 0.02278 0.01499 -0.0870 0.7103 0.0300
-8.000 -0.4352 0.02203 0.01405 -0.0868 0.7017 0.0315
-7.750 -0.4108 0.02120 0.01297 -0.0865 0.6934 0.0331
-7.500 -0.3865 0.02038 0.01204 -0.0863 0.6859 0.0345
-7.250 -0.3614 0.01983 0.01140 -0.0862 0.6786 0.0362
-7.000 -0.3357 0.01933 0.01076 -0.0860 0.6722 0.0386
-6.750 -0.3099 0.01874 0.01003 -0.0859 0.6659 0.0410
-6.500 -0.2843 0.01822 0.00945 -0.0858 0.6606 0.0433
-6.250 -0.2579 0.01779 0.00892 -0.0858 0.6556 0.0464
-6.000 -0.2315 0.01732 0.00836 -0.0857 0.6503 0.0498
-5.750 -0.2051 0.01692 0.00791 -0.0857 0.6455 0.0534
-5.500 -0.1781 0.01660 0.00746 -0.0857 0.6412 0.0577
-5.250 -0.1514 0.01617 0.00704 -0.0857 0.6363 0.0625
-5.000 -0.1241 0.01589 0.00667 -0.0858 0.6321 0.0680
-4.750 -0.0971 0.01556 0.00631 -0.0858 0.6285 0.0743
-4.500 -0.0695 0.01532 0.00598 -0.0859 0.6251 0.0817
-4.250 -0.0421 0.01501 0.00571 -0.0860 0.6211 0.0908
-4.000 -0.0144 0.01476 0.00544 -0.0861 0.6172 0.1012
-3.750 0.0132 0.01453 0.00520 -0.0863 0.6137 0.1146
-3.250 0.0689 0.01411 0.00482 -0.0866 0.6073 0.1522
-3.000 0.0968 0.01388 0.00466 -0.0869 0.6040 0.1776
-2.750 0.1247 0.01366 0.00452 -0.0871 0.6009 0.2101
-2.500 0.1525 0.01340 0.00439 -0.0874 0.5979 0.2543
-2.250 0.1800 0.01308 0.00427 -0.0877 0.5953 0.3218
-2.000 0.2073 0.01268 0.00422 -0.0879 0.5921 0.4176
-1.750 0.2341 0.01234 0.00424 -0.0879 0.5890 0.5185
-1.500 0.2606 0.01213 0.00430 -0.0876 0.5861 0.6013
-1.250 0.2867 0.01204 0.00438 -0.0871 0.5835 0.6638
-1.000 0.3126 0.01203 0.00446 -0.0864 0.5811 0.7132
-0.750 0.3385 0.01208 0.00453 -0.0858 0.5789 0.7525
-0.500 0.3641 0.01213 0.00465 -0.0850 0.5758 0.7823
-0.250 0.3898 0.01220 0.00474 -0.0844 0.5728 0.8064
0.000 0.4152 0.01228 0.00483 -0.0836 0.5702 0.8275
0.250 0.4403 0.01238 0.00491 -0.0828 0.5678 0.8487
0.500 0.4626 0.01247 0.00501 -0.0812 0.5656 0.8732
0.750 0.4849 0.01257 0.00507 -0.0797 0.5635 0.8961
1.000 0.5088 0.01262 0.00514 -0.0787 0.5608 0.9106
1.250 0.5339 0.01267 0.00520 -0.0780 0.5579 0.9225
1.500 0.5602 0.01272 0.00525 -0.0776 0.5554 0.9338
1.750 0.5875 0.01277 0.00529 -0.0775 0.5530 0.9452
2.000 0.6168 0.01283 0.00532 -0.0778 0.5507 0.9560
2.250 0.6491 0.01290 0.00535 -0.0788 0.5485 0.9656
2.500 0.6827 0.01300 0.00544 -0.0802 0.5460 0.9754
2.750 0.7174 0.01311 0.00559 -0.0819 0.5432 0.9859
3.000 0.7514 0.01321 0.00572 -0.0835 0.5404 1.0000
3.250 0.7780 0.01336 0.00587 -0.0836 0.5377 1.0000
3.500 0.8057 0.01351 0.00601 -0.0838 0.5353 1.0000
3.750 0.8339 0.01367 0.00616 -0.0842 0.5331 1.0000
4.000 0.8621 0.01386 0.00635 -0.0845 0.5308 1.0000
4.250 0.8895 0.01406 0.00663 -0.0848 0.5276 1.0000
4.500 0.9173 0.01425 0.00687 -0.0850 0.5246 1.0000
4.750 0.9454 0.01443 0.00708 -0.0853 0.5217 1.0000
5.000 0.9737 0.01459 0.00728 -0.0857 0.5191 1.0000
5.250 1.0024 0.01477 0.00745 -0.0860 0.5168 1.0000
5.500 1.0292 0.01500 0.00779 -0.0861 0.5132 1.0000
5.750 1.0561 0.01519 0.00808 -0.0862 0.5091 1.0000
6.000 1.0836 0.01533 0.00826 -0.0864 0.5050 1.0000
6.250 1.1117 0.01541 0.00832 -0.0865 0.5008 1.0000
6.500 1.1366 0.01555 0.00863 -0.0863 0.4936 1.0000
6.750 1.1635 0.01559 0.00869 -0.0862 0.4875 1.0000
7.000 1.1890 0.01574 0.00895 -0.0860 0.4809 1.0000
7.250 1.2147 0.01583 0.00911 -0.0857 0.4736 1.0000
7.500 1.2397 0.01596 0.00934 -0.0854 0.4652 1.0000
7.750 1.2648 0.01604 0.00944 -0.0850 0.4562 1.0000
8.000 1.2884 0.01622 0.00975 -0.0845 0.4448 1.0000
8.250 1.3119 0.01640 0.01002 -0.0840 0.4329 1.0000
8.500 1.3343 0.01662 0.01030 -0.0832 0.4183 1.0000
8.750 1.3546 0.01690 0.01057 -0.0821 0.3977 1.0000
9.000 1.3710 0.01736 0.01095 -0.0805 0.3667 1.0000
9.250 1.3799 0.01822 0.01160 -0.0778 0.3241 1.0000
9.500 1.3808 0.01952 0.01265 -0.0742 0.2805 1.0000
9.750 1.3757 0.02102 0.01396 -0.0699 0.2453 1.0000
10.000 1.3704 0.02280 0.01560 -0.0662 0.2153 1.0000
10.250 1.3648 0.02488 0.01758 -0.0633 0.1900 1.0000
10.500 1.3603 0.02725 0.01988 -0.0613 0.1677 1.0000
10.750 1.3557 0.02992 0.02249 -0.0599 0.1486 1.0000
11.000 1.3527 0.03266 0.02519 -0.0589 0.1312 1.0000
11.250 1.3497 0.03549 0.02801 -0.0581 0.1159 1.0000
11.500 1.3470 0.03835 0.03085 -0.0573 0.1023 1.0000
11.750 1.3444 0.04121 0.03369 -0.0566 0.0906 1.0000
12.000 1.3420 0.04408 0.03654 -0.0559 0.0801 1.0000
12.250 1.3394 0.04696 0.03942 -0.0552 0.0711 1.0000
12.500 1.3381 0.04973 0.04221 -0.0546 0.0630 1.0000
12.750 1.3371 0.05250 0.04500 -0.0540 0.0562 1.0000
13.000 1.3349 0.05543 0.04794 -0.0535 0.0504 1.0000
13.250 1.3350 0.05820 0.05077 -0.0532 0.0451 1.0000
13.500 1.3342 0.06114 0.05374 -0.0528 0.0409 1.0000
13.750 1.3343 0.06402 0.05668 -0.0526 0.0371 1.0000
14.000 1.3329 0.06714 0.05983 -0.0524 0.0341 1.0000
14.250 1.3339 0.07004 0.06282 -0.0524 0.0313 1.0000
14.500 1.3326 0.07324 0.06606 -0.0524 0.0291 1.0000
14.750 1.3316 0.07645 0.06935 -0.0524 0.0274 1.0000
15.000 1.3319 0.07957 0.07257 -0.0525 0.0258 1.0000
15.250 1.3310 0.08288 0.07596 -0.0527 0.0245 1.0000
15.500 1.3287 0.08642 0.07957 -0.0530 0.0234 1.0000
15.750 1.3259 0.09004 0.08327 -0.0534 0.0225 1.0000
16.000 1.3258 0.09335 0.08670 -0.0538 0.0215 1.0000
16.250 1.3249 0.09681 0.09026 -0.0543 0.0206 1.0000
16.500 1.3238 0.10035 0.09389 -0.0549 0.0198 1.0000
16.750 1.3217 0.10405 0.09767 -0.0557 0.0191 1.0000
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Polar data table (+)
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