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

NACA M26 AIRFOIL (m26-il)

NACA M26 AIRFOIL - NACA/Munk M-26 airfoil


Airfoil m26-il
Details Dat file Parser  
(m26-il) NACA M26 AIRFOIL
NACA/Munk M-26 airfoil
Max thickness 8.3% at 40% chord.
Max camber 8.3% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M26 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125200 0.0177800
 0.0250400 0.0288600
 0.0500700 0.0483300
 0.0750900 0.0627900
 0.1001100 0.0757600
 0.1501300 0.0962900
 0.2001600 0.1102000
 0.3001700 0.1232800
 0.4001600 0.1214400
 0.5001500 0.1043000
 0.6001100 0.0820600
 0.7000800 0.0576200
 0.8000500 0.0338800
 0.9000200 0.0140400
 0.9500100 0.0070700
 1.0000000 0.0024000

 0.0000000 0.0000000
 0.0124900 -.0080200
 0.0249900 -.0057300
 0.0500000 0.0011300
 0.0750100 0.0084900
 0.1000200 0.0155600
 0.1500400 0.0269900
 0.2000500 0.0350200
 0.3000600 0.0417800
 0.4000500 0.0384400
 0.5000400 0.0284000
 0.6000200 0.0153600
 0.7000000 0.0027200
 0.7999900 -.0064200
 0.8999900 -.0092600
 0.9499900 -.0069300
 1.0000000 -.0024000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 15 AIRFOILPreviewDetails
GOE 300 (FRIEDRICHSHAFEN G20)PreviewDetails
NACA M23 AIRFOILPreviewDetails
NACA M25 AIRFOILPreviewDetails
GOE 14 AIRFOILPreviewDetails
NACA M20 AIRFOILPreviewDetails
GOE 81 AIRFOILPreviewDetails
GOE 304 (FRIEDRICHSHAFEN G02)PreviewDetails
lrn1007PreviewDetails
NACA6409 9%PreviewDetails

Polars for NACA M26 AIRFOIL (m26-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m26-il50,00096.1 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m26-il50,000514 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m26-il100,000916.6 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   m26-il100,000541.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m26-il200,000978.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   m26-il200,000578.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m26-il500,0009115.7 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m26-il500,000598.7 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m26-il1,000,0009141.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m26-il1,000,0005113.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit