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 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


Airfoil l188root-il
Details Dat file Parser  
(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
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NASA/LANGLEY NLF 0414F AIRFOILPreviewDetails
NACA 65(2)-415PreviewDetails
MH 200 12.97%PreviewDetails
NACA 66(2)-415PreviewDetails
E209 (13.72%)PreviewDetails
S4233-136-84PreviewDetails
MH 201 13.08%PreviewDetails
HQ 3.0/14 AIRFOILPreviewDetails
NACA 65(2)-215PreviewDetails
NACA 63-415 AIRFOILPreviewDetails

Polars for LOCKHEED L-188 ROOT AIRFOIL (l188root-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   l188root-il50,000932.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   l188root-il50,000529.9 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   l188root-il100,000951.1 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   l188root-il100,000548.7 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   l188root-il200,000972.5 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   l188root-il200,000565.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   l188root-il500,000994.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   l188root-il500,000575.8 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   l188root-il1,000,0009104 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   l188root-il1,000,000579.9 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit