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

Fage & Collins 1 (fg1-il)

Fage & Collins 1 - Fage & Collins 1 airfoil


Airfoil fg1-il
Details Dat file Parser  
(fg1-il) Fage & Collins 1
Fage & Collins 1 airfoil
Max thickness 8.2% at 30% chord.
Max camber 3.1% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
Fage & Collins 1
1.0000     0.0040
0.9500     0.0185
0.9000     0.0273
0.8000     0.0451
0.7000     0.0593
0.6000     0.0694
0.5000     0.0761
0.4000     0.0806
0.3000     0.0817
0.2000     0.0775
0.1500     0.0725
0.1000     0.0651
0.0750     0.0590
0.0500     0.0510
0.0250     0.0398
0.0125     0.0315
0.0000     0.0133
0.0125     0.0002
0.0250     0.0000
0.0500     0.0000
0.0750     0.0000
0.1000     0.0000
0.1500     0.0000
0.2000     0.0000
0.3000     0.0000
0.4000     0.0000
0.5000     0.0000
0.6000     0.0000
0.7000     0.0000
0.8000     0.0000
0.9000     0.0000
0.9500     0.0000
1.0000     0.0040
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 564 AIRFOILPreviewDetails
GOE 515 AIRFOILPreviewDetails
N-9PreviewDetails
GOE 507 AIRFOILPreviewDetails
E178 (8.69%)PreviewDetails
SA7025PreviewDetails
GOE 566 AIRFOILPreviewDetails
GOE 622 AIRFOILPreviewDetails
S4110PreviewDetails
E176 (8.83%)PreviewDetails

Polars for Fage & Collins 1 (fg1-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fg1-il50,000937.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fg1-il50,000537.5 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fg1-il100,000957.2 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fg1-il100,000552.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fg1-il200,000978.1 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fg1-il200,000566 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fg1-il500,000993.6 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fg1-il500,000582.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fg1-il1,000,0009104.9 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   fg1-il1,000,000599.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit