LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)
LOCKHEED C-5A BL1256 AIRFOIL - Lockheed-Georgia C-5A transonic wing airfoils
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(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord. Max camber 1.4% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LOCKHEED C-5A BL1256 AIRFOIL
31.0 31.0
0.0000000 0.0000000
0.0024371 0.0084483
0.0049088 0.0122368
0.0073858 0.0153213
0.0098689 0.0175894
0.0198180 0.0244284
0.0397596 0.0322660
0.0597161 0.0380975
0.0796853 0.0422430
0.0996568 0.0460573
0.1196355 0.0489262
0.1396141 0.0517950
0.1595954 0.0543012
0.1795789 0.0565219
0.1995625 0.0587235
0.2495320 0.0628068
0.2995097 0.0657993
0.3495007 0.0670166
0.3995006 0.0670274
0.4495094 0.0658464
0.4995279 0.0633623
0.5495548 0.0597482
0.5995877 0.0553360
0.6496280 0.0499347
0.6996742 0.0437337
0.7497240 0.0370423
0.7997734 0.0304147
0.8498249 0.0235016
0.8998758 0.0166663
0.9499312 0.0092338
1.0000000 0.0010067
0.0000000 0.0000000
0.0025730 -.0097998
0.0051060 -.0142250
0.0076241 -.0166560
0.0101393 -.0187012
0.0201757 -.0235780
0.0402075 -.0278531
0.0602251 -.0302092
0.0802345 -.0314709
0.1002394 -.0321283
0.1202419 -.0324612
0.1402438 -.0327204
0.1602459 -.0330087
0.1802485 -.0333514
0.2002510 -.0336942
0.2502619 -.0351537
0.3002777 -.0372709
0.3502946 -.0395440
0.4003040 -.0408043
0.4503021 -.0405429
0.5002913 -.0391022
0.5502720 -.0365084
0.6002453 -.0329274
0.6502142 -.0287522
0.7001804 -.0242120
0.7501462 -.0196191
0.8001077 -.0144578
0.8500722 -.0096938
0.9000398 -.0053407
0.9500177 -.0023792
1.0000000 -.0010067
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Polars for LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c5e-il | 50,000 | 9 | 31.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 50,000 | 5 | 31.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 100,000 | 9 | 46.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 100,000 | 5 | 42.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 200,000 | 9 | 59.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 200,000 | 5 | 47.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 500,000 | 9 | 67.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 500,000 | 5 | 64.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 1,000,000 | 9 | 77.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 1,000,000 | 5 | 81 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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