LOCKHEED L-188 TIP AIRFOIL (l188tip-il)
LOCKHEED L-188 TIP AIRFOIL - Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8
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(l188tip-il) LOCKHEED L-188 TIP AIRFOIL Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord. Max camber 2.7% at 51.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LOCKHEED L-188 TIP AIRFOIL
46.0 46.0
0.0000000 0.0000000
0.0012180 0.0063710
0.0048660 0.0128060
0.0109260 0.0191720
0.0193690 0.0254000
0.0301540 0.0314430
0.0432270 0.0372700
0.0585260 0.0428600
0.0759760 0.0481930
0.0954920 0.0532570
0.1169780 0.0580400
0.1403300 0.0625240
0.1654350 0.0666980
0.1921690 0.0705400
0.2204040 0.0740280
0.2500000 0.0771360
0.2808140 0.0798310
0.3126970 0.0820810
0.3454920 0.0838470
0.3790390 0.0850910
0.4131760 0.0857510
0.4477360 0.0856860
0.4825500 0.0848960
0.5174500 0.0834030
0.5522640 0.0812490
0.5868240 0.0784770
0.6209610 0.0751420
0.6545090 0.0713060
0.6873030 0.0670290
0.7191860 0.0623740
0.7500000 0.0573970
0.7795960 0.0521400
0.8078310 0.0465720
0.8345650 0.0407400
0.8596700 0.0349630
0.8830220 0.0294130
0.9045090 0.0242110
0.9240240 0.0194450
0.9414740 0.0151750
0.9567730 0.0114470
0.9698460 0.0082900
0.9806310 0.0057140
0.9890740 0.0037240
0.9951340 0.0023150
0.9987820 0.0014770
1.0000000 0.0012000
0.0000000 0.0000000
0.0012180 -.0057030
0.0048660 -.0106080
0.0109260 -.0148520
0.0193690 -.0185160
0.0301540 -.0216630
0.0432270 -.0243500
0.0585260 -.0266320
0.0759760 -.0285550
0.0954920 -.0301650
0.1169780 -.0315020
0.1403300 -.0326000
0.1654350 -.0334880
0.1921690 -.0341880
0.2204040 -.0347140
0.2500000 -.0350740
0.2808140 -.0352670
0.3126970 -.0352870
0.3454920 -.0351230
0.3790390 -.0347550
0.4131760 -.0341430
0.4477360 -.0331600
0.4825500 -.0318200
0.5174500 -.0301590
0.5522640 -.0282230
0.5868240 -.0260650
0.6209610 -.0237460
0.6545090 -.0213280
0.6873030 -.0188810
0.7191860 -.0164760
0.7500000 -.0141850
0.7795960 -.0120980
0.8078310 -.0103640
0.8345650 -.0090480
0.8596700 -.0079370
0.8830220 -.0069450
0.9045090 -.0060350
0.9240240 -.0051850
0.9414740 -.0043890
0.9567730 -.0036510
0.9698460 -.0029780
0.9806310 -.0023860
0.9890740 -.0018920
0.9951340 -.0015170
0.9987820 -.0012810
1.0000000 -.0012000
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Polars for LOCKHEED L-188 TIP AIRFOIL (l188tip-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| l188tip-il | 50,000 | 9 | 35.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 50,000 | 5 | 33.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 100,000 | 9 | 55.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 100,000 | 5 | 53.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 200,000 | 9 | 79.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 200,000 | 5 | 72.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 500,000 | 9 | 109 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 500,000 | 5 | 91.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 1,000,000 | 9 | 127 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 1,000,000 | 5 | 93.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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