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

NACA 0006 (naca0006-il)

NACA 0006 - NACA 0006 airfoil


Airfoil naca0006-il
Details Dat file Parser  
(naca0006-il) NACA 0006
NACA 0006 airfoil
Max thickness 6% at 30% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 0006
1.0000     0.00063
0.9500     0.00403
0.9000     0.00724
0.8000     0.01312
0.7000     0.01832
0.6000     0.02282
0.5000     0.02647
0.4000     0.02902
0.3000     0.03001
0.2500     0.02971
0.2000     0.02869
0.1500     0.02673
0.1000     0.02341
0.0750     0.02100
0.0500     0.01777
0.0250     0.01307
0.0125     0.00947
0.0000     0.00000
0.0125     -0.00947
0.0250     -0.01307
0.0500     -0.01777
0.0750     -0.02100
0.1000     -0.02341
0.1500     -0.02673
0.2000     -0.02869
0.2500     -0.02971
0.3000     -0.03001
0.4000     -0.02902
0.5000     -0.02647
0.6000     -0.02282
0.7000     -0.01832
0.8000     -0.01312
0.9000     -0.00724
0.9500     -0.00403
1.0000     -0.00063
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EPPLER EA 8(-1)-006 AIRFOILPreviewDetails
NACA-M1 AIRFOILPreviewDetails
GOE 444 AIRFOILPreviewDetails
S1010 HPV airfoilPreviewDetails
GOE 443 AIRFOILPreviewDetails
HQ 0/7 AIRFOILPreviewDetails
GOE 445 AIRFOILPreviewDetails
RAF 30 MOD AIRFOILPreviewDetails
HT08PreviewDetails
S9033 (7.5%)PreviewDetails

Polars for NACA 0006 (naca0006-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca0006-il50,000924.9 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0006-il50,000522.8 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0006-il100,000932.9 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0006-il100,000527.3 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0006-il200,000938.9 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0006-il200,000534 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0006-il500,000547.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0006-il1,000,000956.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0006-il1,000,000560.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit