LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Reynolds number: 500,000 Max Cl/Cd: 73.76 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5b-il-500000.txt Download as CSV file: xf-c5b-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL488.2 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5851 0.08989 0.08736 -0.0529 1.0000 0.0328
-11.250 -0.6185 0.08117 0.07857 -0.0588 1.0000 0.0328
-11.000 -0.6489 0.07585 0.07319 -0.0606 1.0000 0.0328
-10.750 -0.6789 0.07217 0.06944 -0.0598 1.0000 0.0328
-10.500 -0.7093 0.06962 0.06682 -0.0568 1.0000 0.0328
-10.250 -0.7409 0.06802 0.06518 -0.0514 1.0000 0.0328
-10.000 -0.7692 0.06620 0.06328 -0.0457 1.0000 0.0328
-9.750 -0.7907 0.06370 0.06065 -0.0413 1.0000 0.0328
-9.500 -0.8219 0.05383 0.05061 -0.0402 0.9986 0.0337
-9.250 -0.8065 0.05097 0.04771 -0.0411 0.9969 0.0341
-9.000 -0.7910 0.04807 0.04469 -0.0421 0.9950 0.0345
-8.750 -0.8133 0.03454 0.02997 -0.0387 0.9903 0.0249
-8.500 -0.8013 0.02966 0.02454 -0.0377 0.9880 0.0236
-8.250 -0.7803 0.02633 0.02073 -0.0376 0.9865 0.0231
-8.000 -0.7537 0.02434 0.01845 -0.0381 0.9854 0.0230
-7.750 -0.7287 0.02291 0.01683 -0.0381 0.9837 0.0231
-7.500 -0.7056 0.02169 0.01547 -0.0376 0.9811 0.0233
-7.250 -0.6786 0.02059 0.01426 -0.0379 0.9792 0.0235
-7.000 -0.6498 0.01961 0.01318 -0.0385 0.9777 0.0238
-6.750 -0.6200 0.01873 0.01222 -0.0393 0.9765 0.0242
-6.500 -0.5888 0.01801 0.01144 -0.0404 0.9754 0.0248
-6.250 -0.5568 0.01737 0.01072 -0.0416 0.9746 0.0256
-6.000 -0.5351 0.01681 0.01010 -0.0405 0.9710 0.0261
-5.750 -0.5090 0.01602 0.00926 -0.0405 0.9684 0.0268
-5.500 -0.4810 0.01515 0.00838 -0.0410 0.9665 0.0284
-5.250 -0.4495 0.01469 0.00792 -0.0421 0.9651 0.0304
-5.000 -0.4163 0.01434 0.00752 -0.0434 0.9640 0.0326
-4.750 -0.3839 0.01369 0.00688 -0.0448 0.9630 0.0367
-4.500 -0.3616 0.01343 0.00659 -0.0438 0.9588 0.0399
-4.250 -0.3332 0.01296 0.00614 -0.0441 0.9556 0.0453
-4.000 -0.3002 0.01257 0.00576 -0.0454 0.9536 0.0538
-3.750 -0.2670 0.01194 0.00540 -0.0469 0.9520 0.1000
-3.500 -0.2336 0.01137 0.00514 -0.0486 0.9508 0.1706
-3.250 -0.2006 0.01068 0.00488 -0.0503 0.9499 0.2695
-3.000 -0.1798 0.01012 0.00472 -0.0493 0.9455 0.3734
-2.750 -0.1543 0.00948 0.00457 -0.0492 0.9421 0.4987
-2.500 -0.1240 0.00905 0.00448 -0.0500 0.9400 0.5927
-2.250 -0.0909 0.00880 0.00443 -0.0511 0.9385 0.6497
-2.000 -0.0565 0.00864 0.00439 -0.0524 0.9373 0.6953
-1.750 -0.0222 0.00850 0.00434 -0.0537 0.9362 0.7284
-1.500 0.0123 0.00839 0.00426 -0.0549 0.9351 0.7508
-1.250 0.0325 0.00840 0.00431 -0.0532 0.9288 0.7642
-1.000 0.0634 0.00831 0.00423 -0.0537 0.9259 0.7768
-0.750 0.0967 0.00817 0.00410 -0.0548 0.9237 0.7881
-0.500 0.1324 0.00795 0.00389 -0.0562 0.9216 0.7994
-0.250 0.1631 0.00772 0.00370 -0.0564 0.9166 0.8098
0.000 0.1917 0.00750 0.00350 -0.0561 0.9098 0.8213
0.250 0.2251 0.00727 0.00329 -0.0569 0.9058 0.8350
0.500 0.2501 0.00714 0.00321 -0.0559 0.8977 0.8481
0.750 0.2814 0.00690 0.00300 -0.0561 0.8905 0.8574
1.000 0.3069 0.00674 0.00284 -0.0552 0.8782 0.8673
1.250 0.3329 0.00659 0.00271 -0.0543 0.8639 0.8772
1.500 0.3592 0.00650 0.00263 -0.0536 0.8501 0.8868
1.750 0.3859 0.00645 0.00258 -0.0531 0.8366 0.8971
2.000 0.4125 0.00641 0.00255 -0.0525 0.8198 0.9050
2.250 0.4390 0.00641 0.00251 -0.0520 0.7999 0.9145
2.500 0.4638 0.00646 0.00250 -0.0510 0.7712 0.9233
2.750 0.4868 0.00660 0.00251 -0.0496 0.7286 0.9332
3.000 0.5058 0.00690 0.00256 -0.0474 0.6703 0.9451
3.250 0.5264 0.00730 0.00270 -0.0457 0.6067 0.9554
3.500 0.5483 0.00784 0.00291 -0.0445 0.5277 0.9657
3.750 0.5705 0.00865 0.00322 -0.0437 0.4147 0.9757
4.000 0.5966 0.00954 0.00359 -0.0439 0.3025 0.9841
4.250 0.6291 0.01036 0.00396 -0.0456 0.2079 0.9881
4.500 0.6623 0.01099 0.00432 -0.0473 0.1538 0.9931
4.750 0.6969 0.01155 0.00466 -0.0493 0.1153 0.9968
5.000 0.7280 0.01205 0.00500 -0.0505 0.0873 1.0000
5.250 0.7396 0.01229 0.00517 -0.0474 0.0769 1.0000
5.500 0.7550 0.01253 0.00540 -0.0450 0.0713 1.0000
5.750 0.7721 0.01283 0.00565 -0.0429 0.0668 1.0000
6.000 0.7904 0.01319 0.00600 -0.0411 0.0631 1.0000
6.250 0.8112 0.01348 0.00632 -0.0398 0.0607 1.0000
6.500 0.8319 0.01383 0.00668 -0.0385 0.0585 1.0000
6.750 0.8522 0.01426 0.00710 -0.0372 0.0561 1.0000
7.000 0.8696 0.01495 0.00781 -0.0353 0.0533 1.0000
7.250 0.8920 0.01527 0.00818 -0.0344 0.0520 1.0000
7.500 0.9135 0.01566 0.00862 -0.0333 0.0502 1.0000
7.750 0.9344 0.01612 0.00910 -0.0322 0.0482 1.0000
8.000 0.9543 0.01667 0.00967 -0.0309 0.0461 1.0000
8.250 0.9696 0.01785 0.01088 -0.0289 0.0435 1.0000
8.500 0.9918 0.01817 0.01126 -0.0280 0.0422 1.0000
8.750 1.0124 0.01864 0.01179 -0.0268 0.0404 1.0000
9.000 1.0321 0.01913 0.01232 -0.0255 0.0385 1.0000
9.250 1.0504 0.01977 0.01295 -0.0241 0.0367 1.0000
9.500 1.0680 0.02082 0.01406 -0.0227 0.0348 1.0000
9.750 1.0878 0.02114 0.01446 -0.0214 0.0334 1.0000
10.000 1.1067 0.02163 0.01502 -0.0200 0.0321 1.0000
10.250 1.1251 0.02210 0.01552 -0.0187 0.0309 1.0000
10.500 1.1425 0.02261 0.01604 -0.0173 0.0298 1.0000
10.750 1.1576 0.02378 0.01725 -0.0156 0.0285 1.0000
11.000 1.1753 0.02424 0.01783 -0.0142 0.0277 1.0000
11.250 1.1921 0.02486 0.01854 -0.0127 0.0267 1.0000
11.500 1.2083 0.02544 0.01920 -0.0111 0.0258 1.0000
11.750 1.2241 0.02595 0.01975 -0.0097 0.0249 1.0000
12.000 1.2382 0.02667 0.02048 -0.0080 0.0241 1.0000
12.250 1.2493 0.02786 0.02177 -0.0061 0.0232 1.0000
12.500 1.2638 0.02856 0.02260 -0.0045 0.0223 1.0000
12.750 1.2780 0.02921 0.02334 -0.0031 0.0212 1.0000
13.000 1.2922 0.02982 0.02398 -0.0017 0.0203 1.0000
13.250 1.3008 0.03098 0.02516 0.0001 0.0194 1.0000
13.500 1.3087 0.03236 0.02670 0.0021 0.0185 1.0000
13.750 1.3177 0.03359 0.02806 0.0037 0.0177 1.0000
14.000 1.3260 0.03485 0.02941 0.0053 0.0169 1.0000
14.250 1.3323 0.03629 0.03092 0.0068 0.0163 1.0000
14.500 1.3305 0.03855 0.03324 0.0088 0.0156 1.0000
14.750 1.3274 0.04111 0.03598 0.0106 0.0152 1.0000
15.000 1.3277 0.04342 0.03849 0.0118 0.0148 1.0000
15.250 1.3259 0.04601 0.04126 0.0128 0.0144 1.0000
15.500 1.3224 0.04891 0.04431 0.0135 0.0140 1.0000
15.750 1.3178 0.05209 0.04763 0.0138 0.0137 1.0000
16.000 1.3118 0.05561 0.05129 0.0136 0.0135 1.0000
16.250 1.3042 0.05960 0.05542 0.0129 0.0133 1.0000
16.500 1.2947 0.06416 0.06011 0.0116 0.0131 1.0000
16.750 1.2821 0.06944 0.06554 0.0096 0.0129 1.0000
17.000 1.2666 0.07558 0.07184 0.0068 0.0129 1.0000
17.250 1.2486 0.08257 0.07899 0.0033 0.0128 1.0000
17.500 1.2267 0.09064 0.08724 -0.0011 0.0127 1.0000
17.750 1.2009 0.09994 0.09674 -0.0064 0.0128 1.0000
18.000 1.1686 0.11102 0.10805 -0.0128 0.0129 1.0000
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Polar data table (+)
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