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

NACA 66-206 (naca66206-il)

NACA 66-206 - NACA 66-206 airfoil


Airfoil naca66206-il
Details Dat file Parser  
(naca66206-il) NACA 66-206
NACA 66-206 airfoil
Max thickness 6% at 45% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 66-206
1.00000     0.00000
0.95012     0.00578
0.90023     0.01182
0.85031     0.01780
0.80034     0.02339
0.75034     0.02848
0.70031     0.03288
0.65026     0.03641
0.60018     0.03886
0.55009     0.04020
0.50000     0.04088
0.44990     0.04095
0.39981     0.04042
0.34971     0.03929
0.29962     0.03754
0.24954     0.03513
0.19947     0.03196
0.14942     0.02791
0.09939     0.02268
0.07439     0.01947
0.04941     0.01572
0.02447     0.01102
0.01202     0.00798
0.00707     0.00622
0.00461     0.00509
0.00000     0.00000
0.00539     -0.00409
0.00793     -0.00482
0.01298     -0.00584
0.02553     -0.00730
0.05059     -0.00940
0.07561     -0.01099
0.10061     -0.01234
0.15058     -0.01445
0.20053     -0.01604
0.25046     -0.01723
0.30038     -0.01810
0.35029     -0.01869
0.40019     -0.01900
0.45010     -0.01905
0.50000     -0.01882
0.54991     -0.01830
0.59982     -0.01744
0.64974     -0.01581
0.69969     -0.01344
0.74966     -0.01058
0.79966     -0.00747
0.84969     -0.00434
0.89977     -0.00148
0.94988     0.00054
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NACA 64-206PreviewDetails
NACA 65-206PreviewDetails
GOE 598 AIRFOILPreviewDetails
NACA 63-206PreviewDetails
AH21 9% version (Andrew Hollom)PreviewDetails
NACA 64-208PreviewDetails
NACA 64-108 AIRFOILPreviewDetails
RAF 25 AIRFOILPreviewDetails
BOEING-VERTOL VR-9 AIRFOILPreviewDetails
PROPFAN CRUISE MISSILE WING AIRFOILPreviewDetails

Polars for NACA 66-206 (naca66206-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca66206-il50,000920.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66206-il50,000522.6 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca66206-il100,000928.4 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66206-il100,000535.9 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca66206-il200,000952.9 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66206-il200,000550.7 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   naca66206-il500,000971.7 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66206-il500,000559.4 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca66206-il1,000,000976.3 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66206-il1,000,000566.5 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit