LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Reynolds number: 200,000 Max Cl/Cd: 59.57 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5e-il-200000.txt Download as CSV file: xf-c5e-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4465 0.08804 0.08435 -0.0323 1.0000 0.0678
-9.250 -0.4256 0.08623 0.08254 -0.0286 1.0000 0.0689
-9.000 -0.5701 0.08597 0.08202 -0.0369 1.0000 0.0670
-8.750 -0.5893 0.08024 0.07618 -0.0398 1.0000 0.0674
-8.500 -0.5659 0.07634 0.07245 -0.0375 1.0000 0.0684
-8.250 -0.5541 0.07387 0.07003 -0.0364 1.0000 0.0694
-8.000 -0.5486 0.07100 0.06716 -0.0365 1.0000 0.0707
-7.750 -0.5471 0.06768 0.06379 -0.0371 1.0000 0.0726
-7.500 -0.5698 0.06459 0.06008 -0.0389 1.0000 0.0784
-7.250 -0.5683 0.05843 0.05394 -0.0385 1.0000 0.0795
-7.000 -0.5563 0.05550 0.05112 -0.0374 1.0000 0.0806
-6.750 -0.5453 0.05349 0.04916 -0.0359 1.0000 0.0823
-6.500 -0.5370 0.05160 0.04724 -0.0343 1.0000 0.0855
-6.250 -0.5434 0.04880 0.04388 -0.0316 1.0000 0.0925
-6.000 -0.5362 0.04636 0.04159 -0.0295 1.0000 0.0939
-5.750 -0.5310 0.04487 0.04016 -0.0270 1.0000 0.0958
-5.500 -0.5180 0.03235 0.02600 -0.0264 0.9977 0.0680
-5.250 -0.4815 0.02933 0.02276 -0.0289 0.9941 0.0658
-5.000 -0.4458 0.02660 0.01962 -0.0310 0.9896 0.0662
-4.750 -0.4087 0.02412 0.01680 -0.0333 0.9855 0.0661
-4.500 -0.3698 0.02219 0.01456 -0.0356 0.9821 0.0664
-4.250 -0.3336 0.02090 0.01302 -0.0373 0.9762 0.0672
-4.000 -0.2958 0.01904 0.01111 -0.0397 0.9727 0.0691
-3.750 -0.2580 0.01830 0.01040 -0.0419 0.9677 0.0721
-3.500 -0.2203 0.01752 0.00955 -0.0439 0.9621 0.0753
-3.250 -0.1790 0.01675 0.00869 -0.0465 0.9587 0.0782
-3.000 -0.1445 0.01573 0.00777 -0.0480 0.9526 0.0823
-2.750 -0.1079 0.01524 0.00731 -0.0497 0.9464 0.0886
-2.500 -0.0705 0.01452 0.00666 -0.0516 0.9418 0.0960
-2.250 -0.0403 0.01415 0.00630 -0.0520 0.9323 0.1048
-2.000 -0.0055 0.01359 0.00583 -0.0533 0.9266 0.1201
-1.750 0.0213 0.01302 0.00542 -0.0532 0.9163 0.1419
-1.500 0.0520 0.01250 0.00505 -0.0537 0.9092 0.1748
-1.250 0.0784 0.01204 0.00477 -0.0535 0.8990 0.2168
-1.000 0.0971 0.01031 0.00464 -0.0523 0.8901 0.6421
-0.750 0.1201 0.01020 0.00480 -0.0502 0.8805 0.7311
-0.500 0.1427 0.01028 0.00497 -0.0482 0.8697 0.7739
-0.250 0.1657 0.01037 0.00508 -0.0461 0.8599 0.8068
0.000 0.1871 0.01047 0.00521 -0.0438 0.8480 0.8324
0.250 0.2095 0.01055 0.00528 -0.0418 0.8364 0.8496
0.500 0.2326 0.01060 0.00529 -0.0400 0.8264 0.8654
0.750 0.2549 0.01063 0.00532 -0.0381 0.8149 0.8806
1.000 0.2769 0.01065 0.00534 -0.0363 0.8038 0.8957
1.250 0.2991 0.01064 0.00529 -0.0342 0.7941 0.9105
1.500 0.3206 0.01061 0.00528 -0.0322 0.7825 0.9268
1.750 0.3448 0.01056 0.00523 -0.0307 0.7704 0.9430
2.000 0.3753 0.01048 0.00511 -0.0304 0.7554 0.9579
2.250 0.4124 0.01038 0.00494 -0.0316 0.7350 0.9709
2.500 0.4530 0.01028 0.00478 -0.0338 0.7141 0.9789
2.750 0.4930 0.01023 0.00469 -0.0362 0.6954 0.9857
3.000 0.5332 0.01017 0.00460 -0.0387 0.6689 0.9932
3.250 0.5726 0.01013 0.00449 -0.0410 0.6363 1.0000
3.500 0.5914 0.01015 0.00442 -0.0394 0.6060 1.0000
3.750 0.6093 0.01026 0.00439 -0.0376 0.5684 1.0000
4.000 0.6261 0.01051 0.00442 -0.0356 0.5123 1.0000
4.250 0.6390 0.01130 0.00457 -0.0331 0.3823 1.0000
4.500 0.6481 0.01310 0.00529 -0.0307 0.1948 1.0000
4.750 0.6672 0.01418 0.00599 -0.0297 0.1459 1.0000
5.000 0.6887 0.01502 0.00666 -0.0289 0.1221 1.0000
5.250 0.7114 0.01576 0.00732 -0.0282 0.1092 1.0000
5.500 0.7343 0.01650 0.00797 -0.0275 0.1019 1.0000
5.750 0.7583 0.01711 0.00856 -0.0270 0.0966 1.0000
6.000 0.7805 0.01806 0.00937 -0.0262 0.0924 1.0000
6.250 0.8051 0.01868 0.01006 -0.0257 0.0890 1.0000
6.500 0.8294 0.01940 0.01076 -0.0252 0.0857 1.0000
6.750 0.8536 0.02029 0.01159 -0.0248 0.0831 1.0000
7.000 0.8783 0.02160 0.01286 -0.0244 0.0805 1.0000
7.250 0.9034 0.02227 0.01364 -0.0240 0.0781 1.0000
7.500 0.9283 0.02306 0.01448 -0.0236 0.0752 1.0000
7.750 0.9527 0.02388 0.01527 -0.0233 0.0724 1.0000
8.000 0.9779 0.02545 0.01682 -0.0232 0.0698 1.0000
8.250 1.0015 0.02621 0.01777 -0.0225 0.0676 1.0000
8.500 1.0253 0.02723 0.01891 -0.0220 0.0653 1.0000
8.750 1.0488 0.02829 0.02004 -0.0216 0.0633 1.0000
9.000 1.0727 0.02968 0.02141 -0.0213 0.0615 1.0000
9.250 1.0939 0.03169 0.02364 -0.0207 0.0598 1.0000
9.500 1.1129 0.03323 0.02550 -0.0195 0.0581 1.0000
9.750 1.1315 0.03488 0.02737 -0.0184 0.0563 1.0000
10.000 1.1504 0.03648 0.02913 -0.0176 0.0549 1.0000
10.250 1.1688 0.03820 0.03096 -0.0167 0.0538 1.0000
10.500 1.1855 0.04037 0.03325 -0.0159 0.0529 1.0000
10.750 1.1967 0.04396 0.03706 -0.0147 0.0522 1.0000
11.000 1.2003 0.04786 0.04132 -0.0127 0.0519 1.0000
11.250 1.2001 0.05126 0.04512 -0.0104 0.0518 1.0000
11.500 1.1963 0.05513 0.04931 -0.0081 0.0518 1.0000
11.750 1.1913 0.05959 0.05402 -0.0061 0.0520 1.0000
12.000 1.1820 0.06247 0.05719 -0.0034 0.0523 1.0000
12.250 0.9737 0.08758 0.08368 -0.0069 0.0634 1.0000
12.500 0.9906 0.08817 0.08422 -0.0058 0.0622 1.0000
12.750 1.0280 0.08748 0.08338 -0.0025 0.0613 1.0000
13.000 0.6356 0.13679 0.13319 -0.0263 0.0865 1.0000
13.250 0.6348 0.13964 0.13605 -0.0270 0.0847 1.0000
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Polar data table (+)
Polar graphs
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