LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)
LOCKHEED C-141 BL426.57 AIRFOIL - Lockheed-Georgia C-141 transonic wing airfoils
| Details | Dat file | Parser | |
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(c141c-il) LOCKHEED C-141 BL426.57 AIRFOIL Lockheed-Georgia C-141 transonic wing airfoils Max thickness 11% at 40.2% chord. Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LOCKHEED C-141 BL426.57 AIRFOIL
33.0 33.0
0.0000000 0.0000000
0.0024080 0.0084810
0.0096070 0.0159680
0.0215300 0.0230560
0.0380600 0.0297340
0.0590400 0.0359600
0.0842660 0.0416910
0.1134950 0.0469250
0.1464470 0.0516510
0.1828040 0.0558650
0.2222160 0.0595500
0.2643030 0.0626430
0.3086600 0.0650060
0.3548590 0.0666620
0.4024560 0.0675460
0.4509930 0.0675070
0.5000000 0.0665240
0.5490110 0.0646000
0.5975470 0.0617980
0.6451440 0.0581690
0.6913440 0.0537880
0.7357000 0.0487900
0.7777870 0.0432470
0.8171990 0.0372200
0.8535550 0.0309600
0.8865070 0.0248720
0.9157360 0.0192250
0.9409620 0.0138660
0.9619410 0.0092650
0.9784710 0.0056400
0.9903930 0.0030250
0.9975930 0.0014520
1.0000000 0.0009270
0.0000000 0.0000000
0.0024080 -.0070090
0.0096070 -.0135980
0.0215300 -.0192530
0.0380600 -.0240350
0.0590400 -.0280820
0.0842660 -.0314960
0.1134950 -.0343670
0.1464470 -.0367730
0.1828040 -.0387430
0.2222160 -.0403120
0.2643030 -.0414920
0.3086600 -.0422490
0.3548590 -.0425510
0.4024560 -.0423350
0.4509930 -.0415300
0.5000000 -.0401980
0.5490110 -.0383450
0.5975470 -.0358620
0.6451440 -.0329810
0.6913440 -.0297910
0.7357000 -.0263390
0.7777870 -.0228700
0.8171990 -.0195020
0.8535550 -.0163080
0.8865070 -.0131380
0.9157360 -.0101450
0.9409620 -.0074510
0.9619410 -.0051580
0.9784710 -.0032990
0.9903930 -.0019730
0.9975930 -.0011880
1.0000000 -.0009270
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Polars for LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c141c-il | 50,000 | 9 | 31.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141c-il | 50,000 | 5 | 30.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141c-il | 100,000 | 9 | 47.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141c-il | 100,000 | 5 | 44.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141c-il | 200,000 | 9 | 66.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141c-il | 200,000 | 5 | 57.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141c-il | 500,000 | 9 | 80.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141c-il | 500,000 | 5 | 62.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141c-il | 1,000,000 | 9 | 83.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141c-il | 1,000,000 | 5 | 76.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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