LOCKHEED C-5A BL0 AIRFOIL (c5a-il)
LOCKHEED C-5A BL0 AIRFOIL - Lockheed-Georgia C-5A transonic wing airfoils
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(c5a-il) LOCKHEED C-5A BL0 AIRFOIL Lockheed-Georgia C-5A transonic wing airfoils Max thickness 13.1% at 40% chord. Max camber 0.7% at 85% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LOCKHEED C-5A BL0 AIRFOIL
31.0 31.0
0.0000000 0.0000000
0.0024662 0.0060003
0.0049476 0.0093025
0.0074333 0.0118483
0.0099212 0.0139863
0.0198849 0.0204449
0.0398416 0.0281331
0.0598078 0.0341333
0.0797819 0.0387293
0.0997602 0.0425716
0.1197435 0.0455483
0.1397268 0.0484987
0.1597121 0.0511135
0.1796996 0.0533356
0.1996871 0.0555578
0.2496638 0.0596990
0.2996463 0.0627991
0.3496348 0.0648375
0.3996294 0.0658045
0.4496279 0.0660632
0.4996347 0.0648517
0.5496448 0.0630606
0.5996597 0.0604251
0.6496783 0.0571130
0.6997023 0.0528586
0.7497316 0.0476611
0.7997669 0.0413868
0.8498083 0.0340335
0.8998585 0.0251293
0.9499188 0.0144084
1.0000000 0.0012891
0.0000000 0.0000000
0.0025552 -.0098082
0.0050712 -.0126413
0.0075821 -.0145710
0.0100912 -.0161904
0.0201190 -.0211286
0.0401606 -.0285220
0.0601944 -.0345164
0.0802217 -.0393713
0.1002445 -.0434197
0.1202620 -.0465232
0.1402795 -.0496266
0.1602948 -.0523492
0.1803079 -.0546749
0.2003210 -.0569919
0.2503438 -.0610340
0.3003593 -.0637928
0.3503676 -.0652734
0.4003684 -.0654090
0.4503620 -.0642661
0.5003483 -.0618453
0.5503282 -.0582788
0.6003021 -.0536345
0.6502695 -.0478416
0.7002328 -.0413427
0.7501936 -.0343782
0.8001516 -.0269141
0.8501087 -.0193053
0.9000686 -.0121834
0.9500340 -.0060301
1.0000000 -.0012891
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Polars for LOCKHEED C-5A BL0 AIRFOIL (c5a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c5a-il | 50,000 | 9 | 27.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 9 | 41.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 5 | 32.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 9 | 44.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 5 | 40.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 9 | 56.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 5 | 55.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 9 | 68.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 5 | 72.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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