LOCKHEED C-141 BL0 AIRFOIL (c141a-il)
LOCKHEED C-141 BL0 AIRFOIL - Lockheed-Georgia C-141 transonic wing airfoils
| Details | Dat file | Parser | |
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(c141a-il) LOCKHEED C-141 BL0 AIRFOIL Lockheed-Georgia C-141 transonic wing airfoils Max thickness 13% at 40.2% chord. Max camber 1.1% at 64.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LOCKHEED C-141 BL0 AIRFOIL
33.0 33.0
0.0000000 0.0000000
0.0024080 0.0108390
0.0096070 0.0192660
0.0215300 0.0271400
0.0380600 0.0344180
0.0590400 0.0411140
0.0842660 0.0472260
0.1134950 0.0527710
0.1464470 0.0577620
0.1828040 0.0621980
0.2222160 0.0660400
0.2643030 0.0692740
0.3086600 0.0718150
0.3548590 0.0735910
0.4024560 0.0744990
0.4509930 0.0744640
0.5000000 0.0734500
0.5490110 0.0714650
0.5975470 0.0685510
0.6451440 0.0647890
0.6913440 0.0602770
0.7357000 0.0551750
0.7777870 0.0491260
0.8171990 0.0422990
0.8535550 0.0351740
0.8865070 0.0282830
0.9157360 0.0216810
0.9409620 0.0156440
0.9619410 0.0104390
0.9784710 0.0062140
0.9903930 0.0030990
0.9975930 0.0011910
1.0000000 0.0005480
0.0000000 0.0000000
0.0024080 -.0076950
0.0096070 -.0155630
0.0215300 -.0227350
0.0380600 -.0289970
0.0590400 -.0344570
0.0842660 -.0391860
0.1134950 -.0432590
0.1464470 -.0467340
0.1828040 -.0496460
0.2222160 -.0520120
0.2643030 -.0538220
0.3086600 -.0550370
0.3548590 -.0556020
0.4024560 -.0554370
0.4509930 -.0544790
0.5000000 -.0527110
0.5490110 -.0501320
0.5975470 -.0468570
0.6451440 -.0428950
0.6913440 -.0384170
0.7357000 -.0336200
0.7777870 -.0290480
0.8171990 -.0247450
0.8535550 -.0204690
0.8865070 -.0164210
0.9157360 -.0127150
0.9409620 -.0092580
0.9619410 -.0062300
0.9784710 -.0037810
0.9903930 -.0019720
0.9975930 -.0009020
1.0000000 -.0005480
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Polars for LOCKHEED C-141 BL0 AIRFOIL (c141a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c141a-il | 50,000 | 9 | 29 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 50,000 | 5 | 27.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 100,000 | 9 | 44.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 100,000 | 5 | 42 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 200,000 | 9 | 62 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 200,000 | 5 | 47.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 500,000 | 9 | 67.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 500,000 | 5 | 59.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 1,000,000 | 9 | 76.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 1,000,000 | 5 | 72.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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