LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Reynolds number: 200,000 Max Cl/Cd: 44.9 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5a-il-200000.txt Download as CSV file: xf-c5a-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL0 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4737 0.10165 0.09808 -0.0401 1.0000 0.0843
-11.250 -0.4824 0.09710 0.09355 -0.0410 1.0000 0.0869
-8.500 -0.9040 0.04178 0.03514 -0.0133 1.0000 0.0455
-8.250 -0.8938 0.03742 0.03060 -0.0114 1.0000 0.0432
-8.000 -0.8824 0.03399 0.02671 -0.0087 1.0000 0.0407
-7.750 -0.8678 0.03144 0.02362 -0.0061 1.0000 0.0390
-7.500 -0.8492 0.02976 0.02171 -0.0046 1.0000 0.0388
-7.250 -0.8297 0.02823 0.02009 -0.0034 1.0000 0.0396
-7.000 -0.8097 0.02697 0.01873 -0.0023 1.0000 0.0404
-6.750 -0.7887 0.02573 0.01739 -0.0011 1.0000 0.0409
-6.500 -0.7675 0.02455 0.01612 0.0000 1.0000 0.0412
-6.250 -0.7468 0.02350 0.01501 0.0012 1.0000 0.0418
-6.000 -0.7267 0.02255 0.01402 0.0025 1.0000 0.0426
-5.750 -0.7071 0.02168 0.01312 0.0039 1.0000 0.0438
-5.500 -0.6878 0.02091 0.01230 0.0052 1.0000 0.0450
-5.250 -0.6686 0.02013 0.01149 0.0065 1.0000 0.0465
-5.000 -0.6507 0.01909 0.01049 0.0077 1.0000 0.0499
-4.750 -0.6304 0.01851 0.00989 0.0087 1.0000 0.0543
-4.500 -0.6100 0.01775 0.00913 0.0095 1.0000 0.0603
-4.250 -0.5883 0.01708 0.00850 0.0102 1.0000 0.0730
-4.000 -0.5679 0.01435 0.00739 0.0094 1.0000 0.3435
-3.750 -0.5458 0.01329 0.00742 0.0098 1.0000 0.5642
-3.500 -0.5233 0.01332 0.00763 0.0108 1.0000 0.6240
-3.250 -0.5010 0.01348 0.00784 0.0118 1.0000 0.6638
-3.000 -0.4684 0.01379 0.00817 0.0109 0.9973 0.6952
-2.750 -0.4297 0.01423 0.00861 0.0089 0.9929 0.7224
-2.500 -0.3944 0.01465 0.00907 0.0077 0.9878 0.7448
-2.250 -0.3586 0.01499 0.00938 0.0061 0.9837 0.7597
-2.000 -0.3252 0.01515 0.00948 0.0048 0.9786 0.7694
-1.750 -0.2880 0.01541 0.00973 0.0028 0.9753 0.7790
-1.500 -0.2588 0.01555 0.00984 0.0025 0.9692 0.7909
-1.250 -0.2235 0.01579 0.01007 0.0010 0.9649 0.8017
-1.000 -0.1925 0.01591 0.01019 0.0003 0.9592 0.8101
-0.750 -0.1581 0.01598 0.01024 -0.0012 0.9538 0.8181
-0.500 -0.1193 0.01609 0.01034 -0.0036 0.9505 0.8250
-0.250 -0.0942 0.01611 0.01037 -0.0031 0.9426 0.8333
0.000 -0.0580 0.01615 0.01042 -0.0048 0.9382 0.8410
0.250 -0.0271 0.01614 0.01044 -0.0054 0.9313 0.8489
0.500 0.0097 0.01599 0.01030 -0.0071 0.9243 0.8559
0.750 0.0456 0.01584 0.01018 -0.0084 0.9178 0.8619
1.000 0.0795 0.01565 0.01000 -0.0097 0.9100 0.8695
1.250 0.1200 0.01541 0.00982 -0.0118 0.9063 0.8742
1.500 0.1478 0.01515 0.00961 -0.0115 0.8956 0.8815
1.750 0.1962 0.01459 0.00909 -0.0150 0.8914 0.8865
2.000 0.2270 0.01411 0.00868 -0.0147 0.8799 0.8922
2.250 0.2674 0.01349 0.00811 -0.0164 0.8708 0.8981
2.500 0.3080 0.01287 0.00755 -0.0180 0.8614 0.9031
2.750 0.3409 0.01239 0.00712 -0.0181 0.8463 0.9087
3.000 0.3743 0.01197 0.00673 -0.0186 0.8291 0.9157
3.250 0.4049 0.01168 0.00647 -0.0184 0.8035 0.9211
3.500 0.4384 0.01146 0.00623 -0.0189 0.7721 0.9272
3.750 0.4697 0.01136 0.00605 -0.0191 0.7337 0.9338
4.000 0.5011 0.01144 0.00598 -0.0193 0.6796 0.9392
4.250 0.5240 0.01167 0.00595 -0.0180 0.6156 0.9477
4.500 0.5482 0.01222 0.00608 -0.0171 0.5216 0.9539
4.750 0.5614 0.01317 0.00633 -0.0145 0.3760 0.9633
5.000 0.5801 0.01458 0.00693 -0.0137 0.2222 0.9712
5.250 0.6079 0.01582 0.00766 -0.0147 0.1428 0.9769
5.500 0.6395 0.01686 0.00849 -0.0162 0.1128 0.9826
5.750 0.6754 0.01759 0.00919 -0.0184 0.1006 0.9872
6.000 0.7107 0.01837 0.00992 -0.0206 0.0931 0.9922
6.250 0.7472 0.01909 0.01064 -0.0229 0.0877 0.9967
6.500 0.7753 0.02009 0.01157 -0.0237 0.0834 1.0000
6.750 0.7824 0.02047 0.01201 -0.0202 0.0814 1.0000
7.000 0.7891 0.02081 0.01241 -0.0165 0.0793 1.0000
7.250 0.7985 0.02126 0.01291 -0.0133 0.0771 1.0000
7.500 0.8137 0.02183 0.01350 -0.0113 0.0744 1.0000
7.750 0.8372 0.02306 0.01466 -0.0110 0.0711 1.0000
8.000 0.8608 0.02408 0.01581 -0.0105 0.0687 1.0000
8.250 0.8835 0.02488 0.01673 -0.0098 0.0659 1.0000
8.500 0.9066 0.02581 0.01775 -0.0093 0.0632 1.0000
8.750 0.9315 0.02715 0.01906 -0.0094 0.0605 1.0000
9.000 0.9543 0.02896 0.02109 -0.0089 0.0580 1.0000
9.250 0.9743 0.03030 0.02269 -0.0077 0.0557 1.0000
9.500 0.9943 0.03180 0.02439 -0.0067 0.0536 1.0000
9.750 1.0133 0.03309 0.02576 -0.0058 0.0514 1.0000
10.000 1.0302 0.03689 0.02971 -0.0052 0.0491 1.0000
10.250 1.0385 0.03824 0.03147 -0.0022 0.0480 1.0000
10.500 1.0441 0.04071 0.03435 0.0008 0.0468 1.0000
10.750 1.0463 0.04339 0.03740 0.0040 0.0456 1.0000
11.000 1.0471 0.04583 0.04014 0.0071 0.0443 1.0000
11.250 1.0520 0.04757 0.04203 0.0095 0.0429 1.0000
11.500 1.0648 0.04887 0.04330 0.0107 0.0416 1.0000
11.750 1.0627 0.05159 0.04614 0.0135 0.0408 1.0000
12.000 1.0484 0.05544 0.05022 0.0172 0.0404 1.0000
12.250 1.0272 0.05952 0.05456 0.0211 0.0402 1.0000
12.500 1.0032 0.06366 0.05894 0.0242 0.0401 1.0000
12.750 0.9793 0.06775 0.06325 0.0263 0.0401 1.0000
13.000 0.9549 0.07208 0.06780 0.0271 0.0401 1.0000
13.250 0.9296 0.07674 0.07267 0.0264 0.0404 1.0000
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Polar data table (+)
Polar graphs
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