LOCKHEED C-5A BL576 AIRFOIL (c5c-il)
LOCKHEED C-5A BL576 AIRFOIL - Lockheed-Georgia C-5A transonic wing airfoils
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(c5c-il) LOCKHEED C-5A BL576 AIRFOIL Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord. Max camber 1.4% at 65% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LOCKHEED C-5A BL576 AIRFOIL
31.0 31.0
0.0000000 0.0000000
0.0024665 0.0057808
0.0049467 0.0091929
0.0074317 0.0117761
0.0099194 0.0138925
0.0198817 0.0203895
0.0398357 0.0283071
0.0598001 0.0344414
0.0797739 0.0389598
0.0997523 0.0426758
0.1197313 0.0463014
0.1397135 0.0493739
0.1596981 0.0520273
0.1796848 0.0543211
0.1996717 0.0565757
0.2496462 0.0609693
0.2996276 0.0641777
0.3496152 0.0663089
0.3996078 0.0675769
0.4496055 0.0679757
0.4996090 0.0673765
0.5496180 0.0658186
0.5996321 0.0633915
0.6496519 0.0599930
0.6996760 0.0558376
0.7497076 0.0503954
0.7997473 0.0435528
0.8497962 0.0351239
0.8998530 0.0253346
0.9499219 0.0134639
1.0000000 0.0010949
0.0000000 0.0000000
0.0025568 -.0097839
0.0050744 -.0128176
0.0075854 -.0147139
0.0100947 -.0163164
0.0201199 -.0206592
0.0401519 -.0261763
0.0601756 -.0302537
0.0801933 -.0333143
0.1002064 -.0355666
0.1202155 -.0371439
0.1402243 -.0386578
0.1602316 -.0399016
0.1802367 -.0407856
0.2002418 -.0416695
0.2502506 -.0431830
0.3002547 -.0438881
0.3502550 -.0439497
0.4002521 -.0434500
0.4502460 -.0423942
0.5002362 -.0406954
0.5502223 -.0383040
0.6002061 -.0355139
0.6501851 -.0318928
0.7001613 -.0277984
0.7501358 -.0233957
0.8001096 -.0188861
0.8500839 -.0144657
0.9000583 -.0100437
0.9500320 -.0055153
1.0000000 -.0010949
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Polars for LOCKHEED C-5A BL576 AIRFOIL (c5c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c5c-il | 50,000 | 9 | 31.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 50,000 | 5 | 30.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 100,000 | 9 | 48.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 100,000 | 5 | 44.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 200,000 | 9 | 67.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 200,000 | 5 | 55.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 500,000 | 9 | 78.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 500,000 | 5 | 62.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 1,000,000 | 9 | 82.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 1,000,000 | 5 | 77.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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