LOCKHEED L-188 ROOT AIRFOIL (l188root-il)
LOCKHEED L-188 ROOT AIRFOIL - Lockheed L-188/P-3 root airfoil NACA 0014 -1.10 40/1.051 Cli=.3 a=.8
| Details | Dat file | Parser | |
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(l188root-il) LOCKHEED L-188 ROOT AIRFOIL Lockheed L-188/P-3 root airfoil NACA 0014 -1.10 40/1.051 Cli=.3 a=.8 Max thickness 14% at 41.3% chord. Max camber 2% at 51.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LOCKHEED L-188 ROOT AIRFOIL
46.0 46.0
0.0000000 0.0000000
0.0012180 0.0072930
0.0048660 0.0144820
0.0109260 0.0214680
0.0193690 0.0282000
0.0301540 0.0346460
0.0432270 0.0407910
0.0585260 0.0466220
0.0759760 0.0521340
0.0954920 0.0573230
0.1169780 0.0621830
0.1403300 0.0667110
0.1654350 0.0708960
0.1921690 0.0747230
0.2204040 0.0781760
0.2500000 0.0812280
0.2808140 0.0838520
0.3126970 0.0860120
0.3454920 0.0876710
0.3790390 0.0887870
0.4131760 0.0892790
0.4477360 0.0889190
0.4825500 0.0877170
0.5174500 0.0857210
0.5522640 0.0829950
0.5868240 0.0796110
0.6209610 0.0756540
0.6545090 0.0712110
0.6873030 0.0663720
0.7191860 0.0612230
0.7500000 0.0558430
0.7795960 0.0502980
0.8078310 0.0445910
0.8345650 0.0387820
0.8596700 0.0331260
0.8830220 0.0277660
0.9045090 0.0227970
0.9240240 0.0182880
0.9414740 0.0142850
0.9567730 0.0108170
0.9698460 0.0078970
0.9806310 0.0055270
0.9890740 0.0037050
0.9951340 0.0024170
0.9987820 0.0016530
1.0000000 0.0014000
0.0000000 0.0000000
0.0012180 -.0067930
0.0048660 -.0128340
0.0109260 -.0182280
0.0193690 -.0230360
0.0301540 -.0273100
0.0432270 -.0311010
0.0585260 -.0344520
0.0759760 -.0374060
0.0954920 -.0400030
0.1169780 -.0422810
0.1403300 -.0442670
0.1654350 -.0459880
0.1921690 -.0474590
0.2204040 -.0486900
0.2500000 -.0496820
0.2808140 -.0504300
0.3126970 -.0509180
0.3454920 -.0511270
0.3790390 -.0510350
0.4131760 -.0505730
0.4477360 -.0495250
0.4825500 -.0479110
0.5174500 -.0457870
0.5522640 -.0432250
0.5868240 -.0403030
0.6209610 -.0371060
0.6545090 -.0337290
0.6873030 -.0302620
0.7191860 -.0267990
0.7500000 -.0234350
0.7795960 -.0202660
0.8078310 -.0174350
0.8345650 -.0150140
0.8596700 -.0128560
0.8830220 -.0109140
0.9045090 -.0091650
0.9240240 -.0075940
0.9414740 -.0061970
0.9567730 -.0049690
0.9698460 -.0039130
0.9806310 -.0030310
0.9890740 -.0023310
0.9951340 -.0018190
0.9987820 -.0015050
1.0000000 -.0014000
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Polars for LOCKHEED L-188 ROOT AIRFOIL (l188root-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| l188root-il | 50,000 | 9 | 32.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 50,000 | 5 | 29.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 100,000 | 5 | 48.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 200,000 | 9 | 72.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 200,000 | 5 | 65.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 500,000 | 9 | 94.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 500,000 | 5 | 75.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 1,000,000 | 9 | 104 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 1,000,000 | 5 | 79.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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