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

NACA M9 AIRFOIL (m9-il)

NACA M9 AIRFOIL - NACA/Munk M-9 airfoil


Airfoil m9-il
Details Dat file Parser  
(m9-il) NACA M9 AIRFOIL
NACA/Munk M-9 airfoil
Max thickness 10.4% at 15% chord.
Max camber 7.2% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M9 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0312000
 0.0250000 0.0459000
 0.0500000 0.0639000
 0.0750000 0.0779000
 0.1000000 0.0885000
 0.1500000 0.1011000
 0.2000000 0.1075000
 0.2500000 0.1111000
 0.3000000 0.1110000
 0.4000000 0.1024000
 0.5000000 0.0878000
 0.6000000 0.0695000
 0.7000000 0.0484000
 0.8000000 0.0294000
 0.9000000 0.0122000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0083000
 0.0250000 -.0112000
 0.0500000 -.0122000
 0.0750000 -.0107000
 0.1000000 -.0079000
 0.1500000 -.0029000
 0.2000000 0.0053000
 0.2500000 0.0226000
 0.3000000 0.0326000
 0.4000000 0.0391000
 0.5000000 0.0346000
 0.6000000 0.0278000
 0.7000000 0.0172000
 0.8000000 0.0073000
 0.9000000 0.0000000
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 29B AIRFOILPreviewDetails
NACA M8 AIRFOILPreviewDetails
GOE 207 (AVIATIK V8) AIRFOILPreviewDetails
GOE 239 (MVA H.31) AIRFOILPreviewDetails
GOE 176 (ALBATROS 7020) AIRFOILPreviewDetails
GOE 164 (MVA MK.10) AIRFOILPreviewDetails
GOE 363 AIRFOILPreviewDetails
GOE 14 AIRFOILPreviewDetails
GOE 364 AIRFOILPreviewDetails
GOE 301 (FRIEDRICHSHAFEN G 13)PreviewDetails

Polars for NACA M9 AIRFOIL (m9-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m9-il50,000915.4 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m9-il50,000530.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m9-il100,000943.5 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m9-il100,000549.5 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   m9-il200,000963.1 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m9-il200,000563.8 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m9-il500,000980.4 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m9-il500,000581.2 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m9-il1,000,000999.5 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   m9-il1,000,000599.7 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit