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

NACA M21 AIRFOIL (m21-il)

NACA M21 AIRFOIL - NACA/Munk M-21 airfoil


Airfoil m21-il
Details Dat file Parser  
(m21-il) NACA M21 AIRFOIL
NACA/Munk M-21 airfoil
Max thickness 12% at 30% chord.
Max camber 6% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M21 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0221000
 0.0250000 0.0336000
 0.0500000 0.0518000
 0.0750000 0.0662000
 0.1000000 0.0782000
 0.1500000 0.0965000
 0.2000000 0.1090000
 0.3000000 0.1202000
 0.4000000 0.1178000
 0.5000000 0.1055000
 0.6000000 0.0868000
 0.7000000 0.0649000
 0.8000000 0.0421000
 0.9000000 0.0202000
 0.9500000 0.0105000
 1.0000000 0.0024000

 0.0000000 0.0000000
 0.0125000 -.0151000
 0.0250000 -.0186000
 0.0500000 -.0185000
 0.0750000 -.0149700
 0.1000000 -.0113000
 0.1500000 -.0065000
 0.2000000 -.0026000
 0.3000000 0.0007000
 0.4000000 -.0011000
 0.5000000 -.0057000
 0.6000000 -.0114000
 0.7000000 -.0156000
 0.8000000 -.0165000
 0.9000000 -.0127000
 0.9500000 -.0087000
 1.0000000 -.0024000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NACA M24 AIRFOILPreviewDetails
GOE 320 (HANSA-BRANDENBURG II.1)PreviewDetails
NACA 6412PreviewDetails
GOE 332 (PFALZ 61) AIRFOILPreviewDetails
St. CYR 24 (Bartel 35-IIIC)PreviewDetails
GOE 322 (HANSA-BRANDENBURG IV.1)PreviewDetails
GOE 324 (HANSA-BRANDENBURG) AIRFOILPreviewDetails
GOE 528 AIRFOILPreviewDetails
GOE 480 AIRFOILPreviewDetails
GOE 406 AIRFOILPreviewDetails

Polars for NACA M21 AIRFOIL (m21-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m21-il50,00095.4 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m21-il50,000522.2 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m21-il100,000929.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   m21-il100,000548.5 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m21-il200,000970.1 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m21-il200,000573.7 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m21-il500,0009107.3 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m21-il500,0005105.8 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m21-il1,000,0009135.9 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m21-il1,000,0005128.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit