LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Reynolds number: 500,000 Max Cl/Cd: 67.28 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5e-il-500000.txt Download as CSV file: xf-c5e-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL1256 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5932 0.08094 0.07844 -0.0276 1.0000 0.0299
-9.500 -0.5926 0.07687 0.07439 -0.0312 1.0000 0.0302
-9.250 -0.7849 0.03397 0.02996 -0.0429 1.0000 0.0278
-9.000 -0.7871 0.02896 0.02422 -0.0403 1.0000 0.0291
-8.750 -0.7782 0.02598 0.02088 -0.0386 1.0000 0.0298
-8.500 -0.7594 0.02515 0.02003 -0.0375 1.0000 0.0304
-8.250 -0.7398 0.02459 0.01943 -0.0364 1.0000 0.0309
-8.000 -0.7204 0.02398 0.01879 -0.0352 1.0000 0.0315
-7.750 -0.7021 0.02310 0.01781 -0.0338 1.0000 0.0322
-7.500 -0.6846 0.02209 0.01665 -0.0323 1.0000 0.0330
-7.250 -0.6676 0.02123 0.01562 -0.0306 1.0000 0.0338
-7.000 -0.6349 0.02052 0.01470 -0.0320 0.9979 0.0346
-6.750 -0.6015 0.01857 0.01255 -0.0339 0.9954 0.0356
-6.500 -0.5655 0.01780 0.01178 -0.0361 0.9928 0.0366
-6.250 -0.5303 0.01725 0.01120 -0.0379 0.9889 0.0376
-6.000 -0.4938 0.01670 0.01061 -0.0400 0.9855 0.0389
-5.750 -0.4561 0.01608 0.00988 -0.0422 0.9829 0.0401
-5.500 -0.4215 0.01552 0.00924 -0.0436 0.9772 0.0409
-5.250 -0.3872 0.01433 0.00796 -0.0452 0.9724 0.0420
-5.000 -0.3553 0.01350 0.00714 -0.0462 0.9642 0.0431
-4.750 -0.3215 0.01292 0.00656 -0.0475 0.9569 0.0442
-4.500 -0.2917 0.01242 0.00605 -0.0479 0.9446 0.0453
-4.250 -0.2629 0.01198 0.00556 -0.0479 0.9317 0.0466
-4.000 -0.2352 0.01160 0.00513 -0.0478 0.9183 0.0478
-3.750 -0.2083 0.01127 0.00473 -0.0474 0.9049 0.0489
-3.500 -0.1829 0.01068 0.00413 -0.0469 0.8922 0.0514
-3.250 -0.1563 0.01045 0.00387 -0.0465 0.8800 0.0538
-3.000 -0.1294 0.01026 0.00363 -0.0462 0.8681 0.0565
-2.750 -0.1029 0.00994 0.00328 -0.0459 0.8571 0.0602
-2.500 -0.0758 0.00976 0.00309 -0.0456 0.8466 0.0644
-2.250 -0.0484 0.00955 0.00286 -0.0454 0.8367 0.0697
-2.000 -0.0209 0.00941 0.00271 -0.0452 0.8281 0.0778
-1.750 0.0067 0.00919 0.00257 -0.0451 0.8182 0.0938
-1.500 0.0341 0.00902 0.00246 -0.0450 0.8076 0.1164
-1.250 0.0615 0.00891 0.00236 -0.0448 0.7961 0.1361
-1.000 0.0893 0.00875 0.00227 -0.0447 0.7858 0.1573
-0.750 0.1171 0.00861 0.00219 -0.0447 0.7777 0.1875
-0.500 0.1424 0.00742 0.00193 -0.0450 0.7692 0.4762
-0.250 0.1681 0.00696 0.00198 -0.0446 0.7605 0.6416
0.000 0.1955 0.00687 0.00199 -0.0443 0.7490 0.6843
0.250 0.2226 0.00681 0.00202 -0.0438 0.7368 0.7175
0.500 0.2497 0.00680 0.00206 -0.0434 0.7253 0.7462
0.750 0.2768 0.00681 0.00211 -0.0429 0.7137 0.7697
1.000 0.3042 0.00683 0.00214 -0.0425 0.6999 0.7883
1.250 0.3315 0.00685 0.00216 -0.0421 0.6847 0.8026
1.500 0.3589 0.00688 0.00219 -0.0418 0.6700 0.8159
1.750 0.3858 0.00695 0.00221 -0.0413 0.6498 0.8297
2.000 0.4118 0.00702 0.00226 -0.0407 0.6281 0.8428
2.250 0.4377 0.00710 0.00232 -0.0400 0.6058 0.8567
2.500 0.4633 0.00722 0.00239 -0.0393 0.5805 0.8690
2.750 0.4885 0.00741 0.00247 -0.0385 0.5470 0.8815
3.000 0.5127 0.00762 0.00256 -0.0375 0.5038 0.8949
3.250 0.5342 0.00801 0.00269 -0.0361 0.4334 0.9071
3.500 0.5538 0.00870 0.00295 -0.0347 0.3268 0.9180
3.750 0.5715 0.00970 0.00335 -0.0331 0.1949 0.9299
4.000 0.5928 0.01015 0.00361 -0.0318 0.1495 0.9430
4.250 0.6156 0.01048 0.00383 -0.0307 0.1243 0.9577
4.500 0.6437 0.01082 0.00406 -0.0309 0.0989 0.9731
4.750 0.6761 0.01134 0.00442 -0.0321 0.0808 0.9904
5.000 0.7057 0.01166 0.00473 -0.0328 0.0739 1.0000
5.250 0.7322 0.01209 0.00512 -0.0327 0.0692 1.0000
5.500 0.7596 0.01237 0.00540 -0.0328 0.0662 1.0000
5.750 0.7862 0.01272 0.00571 -0.0328 0.0634 1.0000
6.000 0.8111 0.01325 0.00622 -0.0324 0.0606 1.0000
6.250 0.8375 0.01357 0.00656 -0.0323 0.0591 1.0000
6.500 0.8635 0.01392 0.00691 -0.0321 0.0572 1.0000
6.750 0.8891 0.01429 0.00727 -0.0319 0.0552 1.0000
7.000 0.9130 0.01484 0.00779 -0.0314 0.0532 1.0000
7.250 0.9358 0.01552 0.00849 -0.0307 0.0517 1.0000
7.500 0.9607 0.01593 0.00893 -0.0303 0.0506 1.0000
7.750 0.9850 0.01639 0.00944 -0.0299 0.0493 1.0000
8.000 1.0088 0.01689 0.00996 -0.0294 0.0479 1.0000
8.250 1.0321 0.01745 0.01051 -0.0288 0.0466 1.0000
8.500 1.0530 0.01830 0.01135 -0.0279 0.0450 1.0000
8.750 1.0738 0.01927 0.01238 -0.0270 0.0437 1.0000
9.000 1.0973 0.01973 0.01291 -0.0265 0.0426 1.0000
9.250 1.1200 0.02029 0.01352 -0.0258 0.0413 1.0000
9.500 1.1420 0.02088 0.01416 -0.0251 0.0399 1.0000
9.750 1.1632 0.02157 0.01484 -0.0244 0.0387 1.0000
10.000 1.1806 0.02330 0.01658 -0.0233 0.0371 1.0000
10.250 1.2021 0.02375 0.01714 -0.0224 0.0363 1.0000
10.500 1.2225 0.02443 0.01792 -0.0215 0.0354 1.0000
10.750 1.2420 0.02518 0.01876 -0.0205 0.0344 1.0000
11.000 1.2609 0.02589 0.01951 -0.0195 0.0335 1.0000
11.250 1.2790 0.02658 0.02023 -0.0184 0.0327 1.0000
11.500 1.2958 0.02746 0.02112 -0.0173 0.0320 1.0000
11.750 1.3100 0.02931 0.02305 -0.0160 0.0311 1.0000
12.000 1.3225 0.03005 0.02393 -0.0140 0.0307 1.0000
12.250 1.3344 0.03110 0.02512 -0.0122 0.0302 1.0000
12.500 1.3451 0.03231 0.02646 -0.0104 0.0297 1.0000
12.750 1.3546 0.03362 0.02790 -0.0087 0.0293 1.0000
13.000 1.3628 0.03501 0.02942 -0.0070 0.0288 1.0000
13.250 1.3698 0.03650 0.03104 -0.0053 0.0285 1.0000
13.500 1.3757 0.03810 0.03276 -0.0038 0.0282 1.0000
13.750 1.3806 0.03981 0.03458 -0.0025 0.0279 1.0000
14.000 1.3851 0.04156 0.03644 -0.0014 0.0276 1.0000
14.250 1.3899 0.04328 0.03824 -0.0005 0.0273 1.0000
14.500 1.3945 0.04509 0.04011 0.0002 0.0270 1.0000
14.750 1.3967 0.04729 0.04237 0.0008 0.0267 1.0000
15.000 1.3908 0.05067 0.04589 0.0014 0.0264 1.0000
15.250 1.3803 0.05454 0.04997 0.0016 0.0262 1.0000
15.500 1.3724 0.05813 0.05375 0.0011 0.0260 1.0000
15.750 1.3614 0.06232 0.05814 0.0002 0.0259 1.0000
16.000 1.3471 0.06721 0.06323 -0.0012 0.0258 1.0000
16.250 1.3289 0.07297 0.06919 -0.0034 0.0257 1.0000
16.500 1.3065 0.07980 0.07624 -0.0066 0.0257 1.0000
16.750 1.2793 0.08807 0.08473 -0.0111 0.0256 1.0000
17.000 1.2433 0.09874 0.09564 -0.0174 0.0257 1.0000
17.250 1.1906 0.11409 0.11125 -0.0273 0.0260 1.0000
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Polar data table (+)
Polar graphs
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