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

N-12 (n12-il)

N-12 - N-12 airfoil


Airfoil n12-il
Details Dat file Parser  
(n12-il) N-12
N-12 airfoil
Max thickness 10.5% at 30% chord.
Max camber 0.2% at 15% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
N-12
1.0000     0.0000
0.9500     0.0086
0.9000     0.0138
0.8000     0.0242
0.7000     0.0340
0.6000     0.0418
0.5000     0.0480
0.4000     0.0520
0.3000     0.0528
0.2000     0.0508
0.1500     0.0472
0.1000     0.0392
0.0750     0.0352
0.0500     0.0292
0.0250     0.0210
0.0125     0.0154
0.0000     0.0000
0.0125     -0.0152
0.0250     -0.0200
0.0500     -0.0280
0.0750     -0.0348
0.1000     -0.0386
0.1500     -0.0440
0.2000     -0.0480
0.3000     -0.0518
0.4000     -0.0500
0.5000     -0.0470
0.6000     -0.0418
0.7000     -0.0340
0.8000     -0.0246
0.9000     -0.0134
0.9500     -0.0080
1.0000     0.0000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 429 AIRFOILPreviewDetails
N-14PreviewDetails
MH 110 10.01%PreviewDetails
NPL 9615 AIRFOILPreviewDetails
NPL 9660 AIRFOILPreviewDetails
NASA/AMES A-01 AIRFOILPreviewDetails
LOCKHEED-GEORGIA SUPERCRITICALPreviewDetails
BOEING 707 .08 SPAN AIRFOILPreviewDetails
GIII BL0 AIRFOILPreviewDetails
E186 (10.27%)PreviewDetails

Polars for N-12 (n12-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n12-il50,000928.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n12-il50,000527.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n12-il100,000939 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n12-il100,000536.1 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n12-il200,000946.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   n12-il200,000542.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n12-il500,000953.3 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n12-il500,000555.5 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n12-il1,000,000964.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n12-il1,000,000573.7 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit