LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Reynolds number: 50,000 Max Cl/Cd: 30.49 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5c-il-50000-n5.txt Download as CSV file: xf-c5c-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5480 0.09987 0.09206 -0.0471 1.0000 0.0584
-10.250 -0.5555 0.09486 0.08710 -0.0487 1.0000 0.0582
-10.000 -0.5661 0.08963 0.08194 -0.0506 1.0000 0.0579
-9.750 -0.5815 0.08474 0.07709 -0.0521 1.0000 0.0575
-9.500 -0.6018 0.08049 0.07288 -0.0523 1.0000 0.0571
-9.250 -0.6255 0.07707 0.06947 -0.0505 1.0000 0.0568
-9.000 -0.6473 0.07352 0.06589 -0.0483 1.0000 0.0565
-8.750 -0.6660 0.06984 0.06211 -0.0461 1.0000 0.0563
-8.500 -0.6814 0.06615 0.05826 -0.0437 1.0000 0.0562
-8.250 -0.6928 0.06246 0.05434 -0.0412 1.0000 0.0562
-8.000 -0.6995 0.05883 0.05045 -0.0388 1.0000 0.0563
-7.750 -0.7022 0.05528 0.04656 -0.0364 1.0000 0.0564
-7.500 -0.7011 0.05183 0.04274 -0.0341 1.0000 0.0566
-7.250 -0.6962 0.04854 0.03900 -0.0320 1.0000 0.0569
-7.000 -0.6885 0.04545 0.03537 -0.0299 1.0000 0.0579
-6.750 -0.6764 0.04295 0.03261 -0.0283 1.0000 0.0595
-6.500 -0.6615 0.04108 0.03060 -0.0269 1.0000 0.0615
-6.250 -0.6451 0.03909 0.02835 -0.0255 1.0000 0.0635
-6.000 -0.6269 0.03699 0.02590 -0.0242 1.0000 0.0652
-5.750 -0.6069 0.03510 0.02361 -0.0229 1.0000 0.0678
-5.500 -0.5863 0.03348 0.02173 -0.0218 1.0000 0.0713
-5.250 -0.5656 0.03221 0.02042 -0.0208 1.0000 0.0750
-5.000 -0.5431 0.03090 0.01892 -0.0197 1.0000 0.0787
-4.750 -0.5203 0.02975 0.01757 -0.0187 1.0000 0.0838
-4.500 -0.4988 0.02885 0.01668 -0.0177 1.0000 0.0908
-4.250 -0.4765 0.02790 0.01564 -0.0167 1.0000 0.0984
-4.000 -0.4543 0.02706 0.01470 -0.0157 1.0000 0.1098
-3.750 -0.4325 0.02612 0.01383 -0.0149 1.0000 0.1279
-3.500 -0.4102 0.02510 0.01298 -0.0143 1.0000 0.1596
-3.250 -0.3893 0.02397 0.01222 -0.0138 1.0000 0.2211
-3.000 -0.3694 0.02265 0.01166 -0.0132 1.0000 0.3445
-2.750 -0.3563 0.02144 0.01188 -0.0096 1.0000 0.5881
-2.500 -0.3443 0.02135 0.01228 -0.0045 1.0000 0.7498
-2.250 -0.3258 0.02148 0.01245 -0.0010 1.0000 0.8292
-2.000 -0.2969 0.02169 0.01250 -0.0002 1.0000 0.8840
-1.750 -0.2530 0.02202 0.01260 -0.0029 1.0000 0.9340
-1.500 -0.1682 0.02267 0.01287 -0.0140 1.0000 0.9924
-1.250 -0.1486 0.02253 0.01256 -0.0138 1.0000 1.0000
-1.000 -0.1427 0.02232 0.01222 -0.0109 1.0000 1.0000
-0.750 -0.1335 0.02222 0.01197 -0.0085 1.0000 1.0000
-0.500 -0.1210 0.02221 0.01180 -0.0067 1.0000 1.0000
-0.250 -0.1060 0.02228 0.01174 -0.0053 1.0000 1.0000
0.000 -0.0735 0.02263 0.01193 -0.0072 0.9949 1.0000
0.250 -0.0392 0.02299 0.01216 -0.0095 0.9883 1.0000
0.500 -0.0046 0.02340 0.01246 -0.0117 0.9819 1.0000
0.750 0.0301 0.02382 0.01279 -0.0140 0.9752 1.0000
1.000 0.0625 0.02419 0.01310 -0.0157 0.9675 1.0000
1.250 0.0994 0.02468 0.01353 -0.0183 0.9611 1.0000
1.500 0.1292 0.02500 0.01384 -0.0194 0.9519 1.0000
1.750 0.1643 0.02543 0.01426 -0.0215 0.9443 1.0000
2.000 0.1971 0.02579 0.01464 -0.0231 0.9349 1.0000
2.250 0.2289 0.02611 0.01501 -0.0245 0.9246 1.0000
2.500 0.2672 0.02645 0.01540 -0.0269 0.9152 1.0000
2.750 0.3016 0.02667 0.01570 -0.0286 0.9036 1.0000
3.000 0.3334 0.02685 0.01598 -0.0296 0.8908 1.0000
3.250 0.3657 0.02699 0.01623 -0.0306 0.8777 1.0000
3.750 0.4358 0.02686 0.01641 -0.0328 0.8470 1.0000
4.000 0.4774 0.02621 0.01595 -0.0341 0.8256 1.0000
4.250 0.5170 0.02511 0.01505 -0.0341 0.7972 1.0000
4.500 0.5445 0.02423 0.01432 -0.0322 0.7639 1.0000
4.750 0.5707 0.02362 0.01387 -0.0304 0.7293 1.0000
5.000 0.6043 0.02295 0.01338 -0.0297 0.6904 1.0000
5.250 0.6439 0.02218 0.01261 -0.0295 0.6177 1.0000
5.500 0.6802 0.02231 0.01175 -0.0286 0.4357 1.0000
5.750 0.6870 0.02379 0.01234 -0.0249 0.3108 1.0000
6.000 0.6968 0.02523 0.01323 -0.0222 0.2377 1.0000
6.250 0.7109 0.02654 0.01420 -0.0203 0.1951 1.0000
6.500 0.7282 0.02779 0.01528 -0.0188 0.1699 1.0000
6.750 0.7480 0.02897 0.01639 -0.0177 0.1511 1.0000
7.000 0.7701 0.03012 0.01752 -0.0169 0.1362 1.0000
7.250 0.7966 0.03131 0.01874 -0.0168 0.1251 1.0000
7.500 0.8265 0.03265 0.02004 -0.0172 0.1173 1.0000
7.750 0.8567 0.03397 0.02154 -0.0175 0.1092 1.0000
8.000 0.8867 0.03553 0.02308 -0.0181 0.1029 1.0000
8.250 0.9172 0.03728 0.02512 -0.0184 0.0978 1.0000
8.500 0.9426 0.03896 0.02692 -0.0183 0.0929 1.0000
8.750 0.9662 0.04094 0.02909 -0.0179 0.0886 1.0000
9.000 0.9867 0.04311 0.03167 -0.0169 0.0850 1.0000
9.250 1.0044 0.04510 0.03390 -0.0157 0.0812 1.0000
9.500 1.0230 0.04709 0.03592 -0.0150 0.0780 1.0000
9.750 1.0329 0.04984 0.03918 -0.0127 0.0758 1.0000
10.000 1.0380 0.05269 0.04253 -0.0100 0.0735 1.0000
10.250 1.0413 0.05539 0.04560 -0.0074 0.0711 1.0000
10.500 1.0459 0.05783 0.04828 -0.0052 0.0689 1.0000
10.750 1.0503 0.06037 0.05100 -0.0031 0.0673 1.0000
11.000 1.0528 0.06329 0.05408 -0.0010 0.0663 1.0000
11.250 1.0408 0.06666 0.05774 0.0024 0.0656 1.0000
11.500 1.0201 0.07022 0.06162 0.0062 0.0653 1.0000
11.750 0.9971 0.07415 0.06583 0.0090 0.0650 1.0000
12.000 0.9721 0.07861 0.07053 0.0107 0.0649 1.0000
12.250 0.9457 0.08376 0.07588 0.0109 0.0650 1.0000
12.500 0.9186 0.08979 0.08207 0.0095 0.0652 1.0000
12.750 0.8919 0.09686 0.08925 0.0064 0.0655 1.0000
13.000 0.8667 0.10500 0.09746 0.0019 0.0658 1.0000
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Polar data table (+)
Polar graphs
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