LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Reynolds number: 200,000 Max Cl/Cd: 67.34 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5c-il-200000.txt Download as CSV file: xf-c5c-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4447 0.08807 0.08463 -0.0356 1.0000 0.0762
-9.250 -0.4577 0.08376 0.08036 -0.0360 1.0000 0.0784
-9.000 -0.6655 0.07654 0.07291 -0.0435 1.0000 0.0714
-8.750 -0.6604 0.07454 0.07095 -0.0412 1.0000 0.0722
-8.500 -0.6668 0.07216 0.06857 -0.0387 1.0000 0.0730
-8.250 -0.6746 0.06959 0.06598 -0.0363 1.0000 0.0740
-8.000 -0.6830 0.06678 0.06312 -0.0341 1.0000 0.0753
-7.750 -0.6914 0.06366 0.05989 -0.0320 1.0000 0.0772
-6.750 -0.7196 0.03681 0.03048 -0.0205 1.0000 0.0477
-6.500 -0.7053 0.03288 0.02628 -0.0192 1.0000 0.0460
-6.250 -0.6874 0.02988 0.02288 -0.0179 1.0000 0.0446
-6.000 -0.6668 0.02747 0.02007 -0.0168 1.0000 0.0439
-5.750 -0.6449 0.02565 0.01794 -0.0158 1.0000 0.0439
-5.500 -0.6222 0.02421 0.01625 -0.0149 1.0000 0.0445
-5.250 -0.5992 0.02302 0.01487 -0.0140 1.0000 0.0456
-5.000 -0.5759 0.02205 0.01373 -0.0132 1.0000 0.0470
-4.750 -0.5525 0.02110 0.01264 -0.0124 1.0000 0.0486
-4.500 -0.5296 0.01993 0.01153 -0.0119 1.0000 0.0519
-4.250 -0.5067 0.01943 0.01101 -0.0112 1.0000 0.0559
-4.000 -0.4834 0.01873 0.01029 -0.0107 1.0000 0.0604
-3.750 -0.4567 0.01821 0.00982 -0.0109 0.9993 0.0660
-3.500 -0.4214 0.01766 0.00927 -0.0128 0.9967 0.0733
-3.250 -0.3845 0.01728 0.00893 -0.0150 0.9944 0.0854
-3.000 -0.3505 0.01660 0.00854 -0.0167 0.9913 0.1299
-2.750 -0.3165 0.01562 0.00831 -0.0190 0.9887 0.2742
-2.500 -0.2822 0.01461 0.00834 -0.0212 0.9866 0.4999
-2.250 -0.2480 0.01431 0.00875 -0.0225 0.9844 0.6759
-2.000 -0.2211 0.01427 0.00892 -0.0220 0.9791 0.7509
-1.750 -0.1902 0.01442 0.00924 -0.0220 0.9754 0.8132
-1.500 -0.1657 0.01458 0.00950 -0.0205 0.9705 0.8616
-1.250 -0.1401 0.01474 0.00970 -0.0194 0.9651 0.8974
-1.000 -0.1050 0.01501 0.00994 -0.0205 0.9618 0.9222
-0.750 -0.0750 0.01515 0.01003 -0.0208 0.9561 0.9449
-0.500 -0.0320 0.01537 0.01020 -0.0240 0.9523 0.9630
-0.250 0.0220 0.01568 0.01044 -0.0295 0.9505 0.9803
0.000 0.0853 0.01602 0.01074 -0.0370 0.9502 0.9932
0.250 0.1439 0.01621 0.01089 -0.0437 0.9490 1.0000
0.500 0.1672 0.01610 0.01076 -0.0436 0.9403 1.0000
0.750 0.2095 0.01598 0.01061 -0.0469 0.9345 1.0000
1.000 0.2483 0.01570 0.01032 -0.0491 0.9248 1.0000
1.250 0.3102 0.01525 0.00989 -0.0555 0.9192 1.0000
1.500 0.3456 0.01488 0.00953 -0.0569 0.9093 1.0000
1.750 0.4031 0.01438 0.00907 -0.0624 0.9048 1.0000
2.000 0.4402 0.01393 0.00867 -0.0640 0.8959 1.0000
2.250 0.4987 0.01299 0.00779 -0.0691 0.8891 1.0000
2.500 0.5364 0.01209 0.00693 -0.0700 0.8747 1.0000
2.750 0.5662 0.01147 0.00634 -0.0696 0.8593 1.0000
3.000 0.5918 0.01109 0.00599 -0.0687 0.8437 1.0000
3.250 0.6126 0.01083 0.00577 -0.0668 0.8232 1.0000
3.500 0.6380 0.01050 0.00544 -0.0657 0.7931 1.0000
3.750 0.6696 0.01020 0.00500 -0.0656 0.7387 1.0000
4.000 0.6956 0.01033 0.00473 -0.0645 0.6548 1.0000
4.250 0.7065 0.01091 0.00481 -0.0607 0.5560 1.0000
4.500 0.7079 0.01180 0.00507 -0.0554 0.4385 1.0000
4.750 0.7083 0.01287 0.00550 -0.0502 0.3224 1.0000
5.000 0.7129 0.01398 0.00600 -0.0461 0.2169 1.0000
5.250 0.7236 0.01495 0.00659 -0.0430 0.1601 1.0000
5.500 0.7380 0.01577 0.00718 -0.0406 0.1288 1.0000
5.750 0.7538 0.01656 0.00785 -0.0384 0.1124 1.0000
6.000 0.7697 0.01747 0.00864 -0.0363 0.1033 1.0000
6.250 0.7898 0.01810 0.00931 -0.0349 0.0970 1.0000
6.500 0.8091 0.01908 0.01019 -0.0336 0.0914 1.0000
6.750 0.8315 0.01974 0.01093 -0.0326 0.0873 1.0000
7.000 0.8542 0.02042 0.01163 -0.0317 0.0832 1.0000
7.250 0.8769 0.02126 0.01242 -0.0310 0.0792 1.0000
7.500 0.9017 0.02228 0.01350 -0.0306 0.0757 1.0000
7.750 0.9247 0.02294 0.01426 -0.0298 0.0722 1.0000
8.000 0.9475 0.02367 0.01500 -0.0291 0.0689 1.0000
8.250 0.9745 0.02526 0.01658 -0.0293 0.0656 1.0000
8.500 0.9964 0.02602 0.01754 -0.0282 0.0629 1.0000
8.750 1.0189 0.02700 0.01863 -0.0274 0.0600 1.0000
9.000 1.0418 0.02811 0.01978 -0.0268 0.0577 1.0000
9.250 1.0685 0.03085 0.02263 -0.0272 0.0553 1.0000
9.500 1.0863 0.03217 0.02428 -0.0255 0.0538 1.0000
9.750 1.1034 0.03380 0.02620 -0.0238 0.0518 1.0000
10.000 1.1197 0.03554 0.02817 -0.0222 0.0500 1.0000
10.250 1.1357 0.03741 0.03023 -0.0206 0.0487 1.0000
10.500 1.1491 0.03945 0.03247 -0.0188 0.0476 1.0000
10.750 1.1605 0.04223 0.03540 -0.0172 0.0464 1.0000
11.000 1.1572 0.04702 0.04059 -0.0138 0.0455 1.0000
11.250 1.1525 0.04889 0.04287 -0.0095 0.0448 1.0000
11.500 1.1424 0.05183 0.04619 -0.0050 0.0443 1.0000
11.750 1.1255 0.05486 0.04954 0.0001 0.0439 1.0000
12.000 1.1051 0.05822 0.05320 0.0046 0.0436 1.0000
12.250 1.0816 0.06202 0.05727 0.0084 0.0435 1.0000
12.500 1.0555 0.06634 0.06183 0.0111 0.0435 1.0000
12.750 1.0276 0.07135 0.06706 0.0124 0.0437 1.0000
13.000 0.9989 0.07713 0.07302 0.0120 0.0441 1.0000
13.250 0.9706 0.08378 0.07982 0.0100 0.0446 1.0000
13.500 0.9450 0.09123 0.08736 0.0069 0.0452 1.0000
13.750 0.9273 0.09875 0.09494 0.0039 0.0457 1.0000
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Polar data table (+)
Polar graphs
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