Airfoil Tools
Search 1638 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil Comparison

Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.


Airfoil comparison (cast102-il)
Open full size plan in new window Open paginated plan in new window  
Download PDF file SVG image as text file  
 Clear all

    (cast102-il) CAST 10-2/DOA 2 AIRFOIL

CAST 10-2/DOA 2 transonic airfoil
Max thickness 12.2% at 45.4% chord
Max camber 1.5% at 69.4% chord
Remove
Airfoil details
Airfoil plotter

Drawing Options

Chord width in millimetres
Draw the camber line
X grid size in millimetres
Y grid size in millimetres
Used for printing plan. A4 landscape approx 280mm
Used for printing plan. A4 landscape approx 180mm

Polars for (cast102-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   cast102-il50,000932.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   cast102-il50,000530.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   cast102-il100,000945.8 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   cast102-il100,000543 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   cast102-il200,000964 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   cast102-il200,000555.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   cast102-il500,000985.5 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   cast102-il500,000566.8 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   cast102-il1,000,000993.9 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   cast102-il1,000,000575.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit