Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

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


Airfoil l188tip-il
Details Dat file Parser  
(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
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 548 AIRFOILPreviewDetails
NACA 65(1)-412PreviewDetails
SG6051PreviewDetails
HQ 2.5/12 AIRFOILPreviewDetails
EPPLER E853 AIRFOILPreviewDetails
HQ 3.0/12 AIRFOILPreviewDetails
NREL's S806A Airfoil (modified linePreviewDetails
NACA 63-412 AIRFOILPreviewDetails
HQ 2.0/12 AIRFOILPreviewDetails
MH 201 13.08%PreviewDetails

Polars for LOCKHEED L-188 TIP AIRFOIL (l188tip-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   l188tip-il50,000935.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   l188tip-il50,000533.4 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   l188tip-il100,000955.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   l188tip-il100,000553.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   l188tip-il200,000979.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   l188tip-il200,000572.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   l188tip-il500,0009109 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   l188tip-il500,000591.9 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   l188tip-il1,000,0009127 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   l188tip-il1,000,000593.6 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit