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

NACA M12 (nacam12-il)

NACA M12 - NACA M12 airfoil


Airfoil nacam12-il
Details Dat file Parser  
(nacam12-il) NACA M12
NACA M12 airfoil
Max thickness 11.9% at 30% chord.
Max camber 2% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA M12
1.0000     0.0020
0.9500     0.0107
0.9000     0.0189
0.8000     0.0350
0.7000     0.0498
0.6000     0.0627
0.5000     0.0725
0.4000     0.0786
0.3000     0.0795
0.2000     0.0730
0.1500     0.0661
0.1000     0.0559
0.0750     0.0489
0.0500     0.0401
0.0250     0.0286
0.0125     0.0203
0.0000     0.0000
0.0125     -0.0165
0.0250     -0.0214
0.0500     -0.0272
0.0750     -0.0307
0.1000     -0.0331
0.1500     -0.0300
0.2000     -0.0380
0.3000     -0.0398
0.4000     -0.0396
0.5000     -0.0382
0.6000     -0.0350
0.7000     -0.0300
0.8000     -0.0231
0.9000     -0.0137
0.9500     -0.0081
1.0000     -0.0020
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 676 (= M 12) AIRFOILPreviewDetails
NACA M12 AIRFOILPreviewDetails
TSAGI 12% AIRFOILPreviewDetails
NACA M6PreviewDetails
GOE 677 (= M 6) AIRFOILPreviewDetails
NACA M6 AIRFOILPreviewDetails
NACA 25112PreviewDetails
ONERA OA212 AIRFOILPreviewDetails
CLARK YS AIRFOILPreviewDetails
EH 2.0/12PreviewDetails

Polars for NACA M12 (nacam12-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   nacam12-il50,000931.8 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam12-il50,000533.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam12-il100,000949.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam12-il100,000548.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam12-il200,000966.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam12-il200,000556.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam12-il500,000971.5 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam12-il500,000562.7 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam12-il1,000,000978.3 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam12-il1,000,000571.7 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit