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

FX 63-100 AIRFOIL (fx63100-il)

FX 63-100 AIRFOIL - Wortmann FX 63-100 airfoil


Airfoil fx63100-il
Details Dat file Parser  
(fx63100-il) FX 63-100 AIRFOIL
Wortmann FX 63-100 airfoil
Max thickness 9.9% at 30.8% chord.
Max camber 4.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
FX 63-100 AIRFOIL
       18.       16.

 0.0000000 0.0000000
 0.0090000 0.0200000
 0.0260000 0.0320000
 0.0380000 0.0383000
 0.0670000 0.0498000
 0.1030000 0.0607000
 0.1460000 0.0702000
 0.1960000 0.0781000
 0.2500000 0.0841000
 0.3080000 0.0878000
 0.4020000 0.0886000
 0.5000000 0.0845000
 0.5970000 0.0754000
 0.6910000 0.0627000
 0.8040000 0.0435000
 0.8960000 0.0259000
 0.9480000 0.0149000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0090000 -.0073000
 0.0260000 -.0120000
 0.1030000 -.0161000
 0.1460000 -.0165000
 0.1960000 -.0162000
 0.2500000 -.0148000
 0.3080000 -.0115000
 0.4020000 -.0047000
 0.5000000 0.0023500
 0.5970000 0.0108000
 0.6910000 0.0171000
 0.8040000 0.0202000
 0.8960000 0.0165000
 0.9480000 0.0110000
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

RAF 32 MOD AIRFOILPreviewDetails
MH 116 9.84%PreviewDetails
EPPLER 66 AIRFOILPreviewDetails
S4062-095-87PreviewDetails
PSU 94-097 (AIAA 2001-2478)PreviewDetails
GOE 602 MOD. AIRFOILPreviewDetails
MH 38 9.68%PreviewDetails
DAE-51 AIRFOILPreviewDetails
GOE 547 AIRFOILPreviewDetails
GOE 496 AIRFOILPreviewDetails

Polars for FX 63-100 AIRFOIL (fx63100-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx63100-il50,000943 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63100-il50,000544.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63100-il100,000967 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63100-il100,000567.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63100-il200,000992.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63100-il200,000590 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63100-il500,0009121.7 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63100-il500,0005106.2 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63100-il1,000,0009136.5 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63100-il1,000,0005115.4 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit