LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il)
LOCKHEED C-5A BL488.2 AIRFOIL - Lockheed-Georgia C-5A transonic wing airfoils
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(c5b-il) LOCKHEED C-5A BL488.2 AIRFOIL Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.5% at 40% chord. Max camber 1.2% at 70% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LOCKHEED C-5A BL488.2 AIRFOIL
31.0 31.0
0.0000000 0.0000000
0.0024659 0.0058770
0.0049469 0.0091436
0.0074314 0.0118045
0.0099194 0.0138800
0.0198817 0.0203586
0.0398359 0.0282452
0.0598005 0.0343399
0.0797731 0.0390588
0.0997515 0.0427696
0.1197323 0.0460823
0.1397147 0.0491068
0.1596994 0.0517404
0.1796862 0.0540166
0.1996730 0.0562826
0.2496481 0.0605668
0.2996296 0.0637534
0.3496169 0.0659417
0.3996100 0.0671318
0.4496083 0.0674223
0.4996118 0.0668140
0.5496212 0.0652075
0.5996357 0.0627023
0.6496549 0.0593981
0.6996799 0.0550969
0.7497113 0.0496983
0.7997502 0.0430041
0.8497968 0.0349791
0.8998534 0.0252297
0.9499178 0.0141421
1.0000000 0.0011019
0.0000000 0.0000000
0.0025565 -.0097227
0.0050746 -.0128480
0.0075859 -.0147784
0.0100950 -.0163595
0.0201211 -.0208452
0.0401552 -.0267133
0.0601812 -.0311924
0.0802010 -.0346046
0.1002166 -.0372772
0.1202276 -.0391819
0.1402384 -.0410256
0.1602476 -.0426161
0.1802548 -.0438599
0.2002620 -.0451036
0.2502742 -.0471946
0.3002807 -.0483178
0.3502832 -.0487387
0.4002810 -.0483625
0.4502746 -.0472698
0.5002637 -.0453804
0.5502486 -.0427921
0.6002295 -.0395050
0.6502064 -.0355192
0.7001786 -.0307432
0.7501496 -.0257513
0.8001195 -.0205656
0.8500899 -.0154753
0.9000604 -.0103920
0.9500326 -.0056078
1.0000000 -.0011019
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Polars for LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c5b-il | 50,000 | 9 | 30.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 50,000 | 5 | 29.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 100,000 | 9 | 46.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 100,000 | 5 | 42.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 200,000 | 9 | 64.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 200,000 | 5 | 50.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 500,000 | 9 | 73.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 500,000 | 5 | 61.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 1,000,000 | 9 | 78.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 1,000,000 | 5 | 77.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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