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

RAF 31 AIRFOIL (raf31-il)

RAF 31 AIRFOIL - RAF-31 airfoil


Airfoil raf31-il
Details Dat file Parser  
(raf31-il) RAF 31 AIRFOIL
RAF-31 airfoil
Max thickness 12.7% at 30% chord.
Max camber 2.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 31 AIRFOIL
       18.       18.

 0.0000000 0.0000000
 0.0125000 0.0178800
 0.0250000 0.0269700
 0.0500000 0.0387300
 0.0750000 0.0470000
 0.1000000 0.0536600
 0.1500000 0.0644900
 0.2000000 0.0723200
 0.2500000 0.0768500
 0.3000000 0.0807800
 0.4000000 0.0812400
 0.5000000 0.0777000
 0.6000000 0.0685600
 0.7000000 0.0550200
 0.8000000 0.0386800
 0.9000000 0.0200400
 0.9500000 0.0113700
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0173200
 0.0250000 -.0228300
 0.0500000 -.0308700
 0.0750000 -.0355000
 0.1000000 -.0389400
 0.1500000 -.0440100
 0.2000000 -.0462800
 0.2500000 -.0471500
 0.3000000 -.0466200
 0.4000000 -.0423600
 0.5000000 -.0363000
 0.6000000 -.0284400
 0.7000000 -.0201800
 0.8000000 -.0121200
 0.9000000 -.0058600
 0.9500000 -.0033300
 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 600 AIRFOILPreviewDetails
PSU-90-125WLPreviewDetails
E201 (11.88%)PreviewDetails
NACA 63-412 AIRFOILPreviewDetails
HQ 2.0/12 AIRFOILPreviewDetails
E203 (13.64%)PreviewDetails
GOE 704 AIRFOILPreviewDetails
HQ 2.5/12 AIRFOILPreviewDetails
RAF 38 AIRFOILPreviewDetails
LDS-2 AIRFOILPreviewDetails

Polars for RAF 31 AIRFOIL (raf31-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf31-il50,000933.8 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf31-il50,000533.5 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   raf31-il100,000953 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf31-il100,000550.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf31-il200,000972.1 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf31-il200,000565 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf31-il500,000993.3 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf31-il500,000579.6 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf31-il1,000,0009106.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf31-il1,000,000583.3 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit