LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Reynolds number: 100,000 Max Cl/Cd: 44.09 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5c-il-100000-n5.txt Download as CSV file: xf-c5c-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL576 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5478 0.09349 0.08798 -0.0450 1.0000 0.0360
-10.250 -0.5655 0.08652 0.08107 -0.0479 1.0000 0.0353
-10.000 -0.6074 0.07439 0.06896 -0.0552 1.0000 0.0342
-9.750 -0.6566 0.06744 0.06192 -0.0558 1.0000 0.0336
-9.500 -0.7010 0.06340 0.05777 -0.0513 1.0000 0.0332
-9.250 -0.7363 0.05865 0.05273 -0.0471 1.0000 0.0328
-9.000 -0.7582 0.05452 0.04826 -0.0431 1.0000 0.0326
-8.750 -0.7676 0.05115 0.04459 -0.0399 1.0000 0.0325
-8.500 -0.7711 0.04803 0.04117 -0.0369 1.0000 0.0326
-8.250 -0.7700 0.04516 0.03797 -0.0343 1.0000 0.0327
-8.000 -0.7650 0.04252 0.03502 -0.0319 1.0000 0.0329
-7.750 -0.7569 0.04010 0.03230 -0.0297 1.0000 0.0332
-7.500 -0.7461 0.03788 0.02978 -0.0278 1.0000 0.0336
-7.250 -0.7328 0.03585 0.02746 -0.0260 1.0000 0.0341
-7.000 -0.7177 0.03396 0.02528 -0.0244 1.0000 0.0347
-6.750 -0.7008 0.03221 0.02323 -0.0230 1.0000 0.0355
-6.500 -0.6825 0.03071 0.02145 -0.0217 1.0000 0.0369
-6.250 -0.6627 0.02938 0.01977 -0.0205 1.0000 0.0386
-6.000 -0.6423 0.02800 0.01822 -0.0195 1.0000 0.0401
-5.750 -0.6216 0.02689 0.01707 -0.0186 1.0000 0.0417
-5.500 -0.6003 0.02593 0.01600 -0.0178 1.0000 0.0436
-5.250 -0.5709 0.02504 0.01494 -0.0184 0.9980 0.0468
-5.000 -0.5417 0.02401 0.01385 -0.0191 0.9959 0.0496
-4.750 -0.5117 0.02321 0.01303 -0.0200 0.9938 0.0529
-4.500 -0.4823 0.02256 0.01228 -0.0207 0.9910 0.0577
-4.250 -0.4527 0.02179 0.01153 -0.0216 0.9883 0.0624
-4.000 -0.4213 0.02126 0.01091 -0.0226 0.9858 0.0694
-3.750 -0.3914 0.02070 0.01040 -0.0235 0.9832 0.0814
-3.500 -0.3629 0.02011 0.00997 -0.0241 0.9800 0.1029
-3.250 -0.3329 0.01954 0.00962 -0.0250 0.9772 0.1489
-3.000 -0.3017 0.01899 0.00936 -0.0264 0.9748 0.2160
-2.750 -0.2729 0.01825 0.00917 -0.0273 0.9722 0.3286
-2.500 -0.2499 0.01726 0.00921 -0.0268 0.9690 0.5366
-2.250 -0.2264 0.01698 0.00957 -0.0251 0.9655 0.6992
-2.000 -0.1978 0.01706 0.00975 -0.0246 0.9624 0.7659
-1.750 -0.1705 0.01713 0.00978 -0.0242 0.9584 0.8007
-1.500 -0.1439 0.01720 0.00982 -0.0236 0.9534 0.8282
-1.250 -0.1125 0.01731 0.00991 -0.0240 0.9497 0.8561
-1.000 -0.0770 0.01749 0.01006 -0.0251 0.9469 0.8892
-0.750 -0.0451 0.01767 0.01023 -0.0254 0.9422 0.9270
-0.500 0.0020 0.01793 0.01043 -0.0291 0.9397 0.9591
-0.250 0.0542 0.01813 0.01056 -0.0343 0.9378 0.9780
0.250 0.1520 0.01833 0.01066 -0.0440 0.9332 0.9975
0.500 0.1755 0.01829 0.01058 -0.0438 0.9252 1.0000
0.750 0.2054 0.01825 0.01052 -0.0447 0.9193 1.0000
1.000 0.2275 0.01822 0.01047 -0.0440 0.9111 1.0000
1.250 0.2580 0.01819 0.01043 -0.0449 0.9048 1.0000
1.750 0.3201 0.01799 0.01026 -0.0464 0.8892 1.0000
2.000 0.3465 0.01783 0.01012 -0.0460 0.8779 1.0000
2.250 0.3808 0.01749 0.00983 -0.0469 0.8664 1.0000
2.500 0.4191 0.01693 0.00932 -0.0481 0.8528 1.0000
2.750 0.4514 0.01641 0.00885 -0.0482 0.8365 1.0000
3.000 0.4785 0.01607 0.00858 -0.0474 0.8197 1.0000
3.250 0.5065 0.01571 0.00826 -0.0468 0.7996 1.0000
3.500 0.5320 0.01540 0.00800 -0.0456 0.7731 1.0000
3.750 0.5667 0.01498 0.00759 -0.0460 0.7381 1.0000
4.000 0.6169 0.01448 0.00688 -0.0491 0.6644 1.0000
4.250 0.6507 0.01476 0.00658 -0.0493 0.5426 1.0000
4.500 0.6632 0.01564 0.00675 -0.0461 0.4168 1.0000
4.750 0.6746 0.01656 0.00714 -0.0432 0.3218 1.0000
5.000 0.6881 0.01746 0.00761 -0.0408 0.2444 1.0000
5.250 0.7034 0.01833 0.00812 -0.0387 0.1885 1.0000
5.500 0.7206 0.01907 0.00869 -0.0370 0.1532 1.0000
5.750 0.7384 0.01979 0.00926 -0.0353 0.1302 1.0000
6.000 0.7563 0.02051 0.00989 -0.0337 0.1157 1.0000
6.250 0.7735 0.02131 0.01062 -0.0319 0.1056 1.0000
6.500 0.7919 0.02204 0.01141 -0.0303 0.0973 1.0000
6.750 0.8089 0.02293 0.01223 -0.0286 0.0907 1.0000
7.000 0.8290 0.02363 0.01303 -0.0273 0.0851 1.0000
7.250 0.8485 0.02446 0.01388 -0.0260 0.0809 1.0000
7.500 0.8678 0.02544 0.01482 -0.0248 0.0774 1.0000
7.750 0.8898 0.02625 0.01578 -0.0239 0.0735 1.0000
8.000 0.9111 0.02711 0.01671 -0.0229 0.0698 1.0000
8.250 0.9318 0.02807 0.01766 -0.0220 0.0670 1.0000
8.500 0.9540 0.02917 0.01889 -0.0213 0.0640 1.0000
8.750 0.9759 0.03022 0.02010 -0.0205 0.0608 1.0000
9.000 0.9964 0.03127 0.02122 -0.0196 0.0581 1.0000
9.250 1.0164 0.03248 0.02239 -0.0188 0.0557 1.0000
9.500 1.0376 0.03398 0.02418 -0.0180 0.0534 1.0000
9.750 1.0573 0.03557 0.02603 -0.0169 0.0512 1.0000
10.000 1.0742 0.03698 0.02762 -0.0156 0.0490 1.0000
10.250 1.0900 0.03829 0.02900 -0.0143 0.0471 1.0000
10.500 1.1067 0.04032 0.03110 -0.0133 0.0455 1.0000
10.750 1.1164 0.04258 0.03382 -0.0110 0.0443 1.0000
11.000 1.1222 0.04508 0.03674 -0.0083 0.0431 1.0000
11.250 1.1238 0.04751 0.03954 -0.0053 0.0419 1.0000
11.500 1.1227 0.04976 0.04207 -0.0020 0.0408 1.0000
11.750 1.1209 0.05185 0.04437 0.0010 0.0397 1.0000
12.000 1.1186 0.05389 0.04659 0.0038 0.0388 1.0000
12.250 1.1160 0.05603 0.04887 0.0062 0.0381 1.0000
12.500 1.1111 0.05859 0.05158 0.0085 0.0375 1.0000
12.750 1.1024 0.06176 0.05491 0.0105 0.0371 1.0000
13.000 1.0833 0.06572 0.05913 0.0126 0.0368 1.0000
13.250 1.0589 0.07040 0.06411 0.0136 0.0367 1.0000
13.500 1.0327 0.07583 0.06981 0.0133 0.0367 1.0000
13.750 1.0050 0.08223 0.07644 0.0114 0.0368 1.0000
14.000 0.9759 0.08986 0.08426 0.0076 0.0369 1.0000
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Polar data table (+)
Polar graphs
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