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

RAF 32 AIRFOIL (raf32-il)

RAF 32 AIRFOIL - RAF-32 airfoil


Airfoil raf32-il
Details Dat file Parser  
(raf32-il) RAF 32 AIRFOIL
RAF-32 airfoil
Max thickness 12.7% at 30% chord.
Max camber 5% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 32 AIRFOIL
       13.       13.

 0.0000000 0.0000000
 0.0250000 0.0318200
 0.0500000 0.0458500
 0.1000000 0.0663000
 0.2000000 0.0916000
 0.3000000 0.1055000
 0.4000000 0.1100000
 0.5000000 0.1069000
 0.6000000 0.0962000
 0.7000000 0.0799000
 0.8000000 0.0578000
 0.9000000 0.0315000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0250000 -.0183700
 0.0500000 -.0237500
 0.1000000 -.0279000
 0.2000000 -.0276000
 0.3000000 -.0213000
 0.4000000 -.0140000
 0.5000000 -.0067000
 0.6000000 0.0002000
 0.7000000 0.0049000
 0.8000000 0.0068000
 0.9000000 0.0047000
 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 497 AIRFOILPreviewDetails
EPPLER 395 AIRFOILPreviewDetails
EPPLER 396 AIRFOILPreviewDetails
GOE 430 AIRFOILPreviewDetails
FX 63-120 AIRFOILPreviewDetails
EPPLER 397 AIRFOILPreviewDetails
GOE 584 AIRFOILPreviewDetails
GOE 532 AIRFOILPreviewDetails
GOE 701 AIRFOILPreviewDetails
GOE 412 AIRFOILPreviewDetails

Polars for RAF 32 AIRFOIL (raf32-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf32-il50,000929.2 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf32-il50,000525.6 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   raf32-il100,000956.2 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf32-il100,000556.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf32-il200,000985.7 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf32-il200,000584.8 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf32-il500,0009123.7 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf32-il500,0005116.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf32-il1,000,0009152.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf32-il1,000,0005134.8 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit