LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Reynolds number: 100,000 Max Cl/Cd: 42.31 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5e-il-100000-n5.txt Download as CSV file: xf-c5e-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5381 0.09323 0.08757 -0.0226 1.0000 0.0465
-9.250 -0.5429 0.08770 0.08207 -0.0262 1.0000 0.0461
-9.000 -0.5530 0.08105 0.07545 -0.0318 1.0000 0.0460
-8.750 -0.5691 0.07502 0.06942 -0.0363 1.0000 0.0459
-8.500 -0.5828 0.06972 0.06403 -0.0387 1.0000 0.0461
-8.250 -0.5922 0.06452 0.05869 -0.0401 1.0000 0.0466
-8.000 -0.5979 0.05945 0.05341 -0.0405 1.0000 0.0469
-7.750 -0.5998 0.05464 0.04836 -0.0402 1.0000 0.0470
-7.500 -0.5993 0.04994 0.04335 -0.0393 1.0000 0.0471
-7.250 -0.5967 0.04535 0.03837 -0.0380 1.0000 0.0474
-7.000 -0.5920 0.04086 0.03337 -0.0364 1.0000 0.0482
-6.750 -0.5815 0.03799 0.03018 -0.0349 1.0000 0.0493
-6.500 -0.5657 0.03678 0.02895 -0.0337 1.0000 0.0503
-6.250 -0.5510 0.03506 0.02707 -0.0323 1.0000 0.0512
-6.000 -0.5367 0.03295 0.02470 -0.0307 1.0000 0.0518
-5.750 -0.5215 0.03102 0.02249 -0.0292 1.0000 0.0526
-5.500 -0.5055 0.02928 0.02047 -0.0276 1.0000 0.0535
-5.250 -0.4764 0.02740 0.01824 -0.0285 0.9962 0.0550
-5.000 -0.4407 0.02567 0.01607 -0.0304 0.9903 0.0575
-4.750 -0.4054 0.02451 0.01491 -0.0325 0.9843 0.0593
-4.500 -0.3708 0.02343 0.01373 -0.0341 0.9777 0.0610
-4.250 -0.3347 0.02235 0.01254 -0.0360 0.9719 0.0631
-4.000 -0.3008 0.02140 0.01143 -0.0373 0.9648 0.0659
-3.750 -0.2649 0.02058 0.01064 -0.0391 0.9589 0.0694
-3.500 -0.2316 0.01995 0.01003 -0.0404 0.9513 0.0731
-3.250 -0.1971 0.01922 0.00925 -0.0418 0.9446 0.0771
-3.000 -0.1655 0.01861 0.00872 -0.0427 0.9364 0.0820
-2.750 -0.1323 0.01811 0.00824 -0.0438 0.9290 0.0893
-2.500 -0.1019 0.01759 0.00780 -0.0444 0.9205 0.0964
-2.250 -0.0699 0.01714 0.00740 -0.0452 0.9127 0.1080
-2.000 -0.0401 0.01675 0.00705 -0.0456 0.9038 0.1228
-1.750 -0.0088 0.01632 0.00671 -0.0464 0.8961 0.1422
-1.500 0.0203 0.01597 0.00644 -0.0467 0.8870 0.1675
-1.250 0.0510 0.01553 0.00613 -0.0473 0.8794 0.2050
-1.000 0.0702 0.01385 0.00601 -0.0464 0.8700 0.5759
-0.750 0.0937 0.01368 0.00625 -0.0443 0.8623 0.7080
-0.500 0.1165 0.01375 0.00643 -0.0424 0.8525 0.7559
-0.250 0.1426 0.01380 0.00649 -0.0411 0.8449 0.7896
0.000 0.1662 0.01390 0.00658 -0.0396 0.8345 0.8143
0.250 0.1912 0.01394 0.00663 -0.0382 0.8263 0.8355
0.500 0.2148 0.01401 0.00670 -0.0367 0.8162 0.8551
0.750 0.2391 0.01405 0.00674 -0.0353 0.8071 0.8754
1.000 0.2632 0.01406 0.00677 -0.0337 0.7976 0.8969
1.250 0.2896 0.01407 0.00679 -0.0326 0.7871 0.9170
1.500 0.3208 0.01402 0.00673 -0.0326 0.7774 0.9330
1.750 0.3521 0.01399 0.00669 -0.0330 0.7643 0.9449
2.000 0.3848 0.01395 0.00663 -0.0337 0.7493 0.9546
2.250 0.4191 0.01390 0.00657 -0.0347 0.7330 0.9636
2.500 0.4536 0.01386 0.00652 -0.0359 0.7156 0.9735
2.750 0.4886 0.01379 0.00642 -0.0370 0.6943 0.9839
3.000 0.5232 0.01371 0.00628 -0.0381 0.6630 0.9953
3.250 0.5471 0.01369 0.00617 -0.0372 0.6287 1.0000
3.500 0.5660 0.01376 0.00611 -0.0353 0.5888 1.0000
3.750 0.5860 0.01394 0.00607 -0.0336 0.5376 1.0000
4.000 0.6054 0.01431 0.00609 -0.0319 0.4601 1.0000
4.250 0.6218 0.01513 0.00629 -0.0300 0.3463 1.0000
4.500 0.6363 0.01645 0.00684 -0.0284 0.2206 1.0000
4.750 0.6556 0.01743 0.00745 -0.0274 0.1695 1.0000
5.000 0.6770 0.01820 0.00804 -0.0266 0.1419 1.0000
5.250 0.6987 0.01892 0.00867 -0.0259 0.1246 1.0000
5.500 0.7206 0.01963 0.00932 -0.0251 0.1125 1.0000
5.750 0.7424 0.02036 0.00999 -0.0243 0.1035 1.0000
6.000 0.7646 0.02103 0.01066 -0.0235 0.0962 1.0000
6.250 0.7860 0.02181 0.01139 -0.0227 0.0909 1.0000
6.500 0.8080 0.02256 0.01214 -0.0219 0.0861 1.0000
6.750 0.8294 0.02341 0.01294 -0.0211 0.0827 1.0000
7.000 0.8510 0.02439 0.01388 -0.0203 0.0801 1.0000
7.250 0.8741 0.02528 0.01486 -0.0197 0.0772 1.0000
7.500 0.8970 0.02618 0.01580 -0.0191 0.0741 1.0000
7.750 0.9195 0.02714 0.01672 -0.0185 0.0715 1.0000
8.000 0.9429 0.02831 0.01788 -0.0181 0.0696 1.0000
8.250 0.9666 0.02941 0.01916 -0.0175 0.0674 1.0000
8.500 0.9893 0.03050 0.02038 -0.0170 0.0649 1.0000
8.750 1.0113 0.03154 0.02147 -0.0164 0.0627 1.0000
9.000 1.0332 0.03274 0.02265 -0.0160 0.0609 1.0000
9.250 1.0542 0.03419 0.02434 -0.0153 0.0590 1.0000
9.500 1.0740 0.03564 0.02602 -0.0145 0.0568 1.0000
9.750 1.0930 0.03704 0.02757 -0.0136 0.0550 1.0000
10.000 1.1113 0.03835 0.02897 -0.0128 0.0535 1.0000
10.250 1.1298 0.03978 0.03041 -0.0122 0.0522 1.0000
10.500 1.1421 0.04195 0.03296 -0.0108 0.0508 1.0000
10.750 1.1520 0.04432 0.03571 -0.0092 0.0495 1.0000
11.000 1.1596 0.04680 0.03851 -0.0075 0.0484 1.0000
11.250 1.1646 0.04930 0.04130 -0.0058 0.0476 1.0000
11.500 1.1671 0.05179 0.04405 -0.0039 0.0468 1.0000
11.750 1.1649 0.05419 0.04667 -0.0017 0.0462 1.0000
12.000 1.1616 0.05665 0.04931 0.0002 0.0457 1.0000
12.250 1.1572 0.05923 0.05205 0.0018 0.0451 1.0000
12.500 1.1525 0.06197 0.05492 0.0029 0.0447 1.0000
12.750 1.1458 0.06513 0.05821 0.0035 0.0443 1.0000
13.000 1.1257 0.06972 0.06304 0.0035 0.0440 1.0000
13.250 1.0979 0.07559 0.06921 0.0020 0.0440 1.0000
13.500 1.0674 0.08264 0.07652 -0.0010 0.0440 1.0000
13.750 1.0343 0.09114 0.08525 -0.0058 0.0441 1.0000
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Polar data table (+)
Polar graphs
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