Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search

Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

(goe63-il) GOE 63 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 63 airfoil Max thickness 8.3% at 19.9% chord Max camber 6.7% at 39.9% chord Source UIUC Airfoil Coordinates Database
(e184-il) E184 (8.33%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E184 low Reynolds number airfoil Max thickness 8.3% at 33.3% chord Max camber 0.8% at 38.3% chord Source UIUC Airfoil Coordinates Database
(m26-il) NACA M26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-26 airfoil Max thickness 8.3% at 40% chord Max camber 8.3% at 30% chord Source UIUC Airfoil Coordinates Database
(giiih-il) GIII BL207 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 39.9% chord Max camber 1.3% at 29.9% chord Source UIUC Airfoil Coordinates Database
(giiig-il) GIII BL167 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord Source UIUC Airfoil Coordinates Database

(giiif-il) GIII BL145 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord Source UIUC Airfoil Coordinates Database
(usa25-il) USA 25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-25 airfoil Max thickness 8.3% at 19.9% chord Max camber 5.2% at 29.9% chord Source UIUC Airfoil Coordinates Database
(goe326-il) GOE 326 (PFALZ 55) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 326 (Pfalz 55) airfoil Max thickness 8.2% at 29.9% chord Max camber 4.7% at 39.9% chord Source UIUC Airfoil Coordinates Database
(m11-il) NACA M11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-11 airfoil Max thickness 8.2% at 30% chord Max camber 1.9% at 30% chord Source UIUC Airfoil Coordinates Database
(goe325-il) GOE 325 (PFALZ 54) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 325 (Pfalz 54) airfoil Max thickness 8.2% at 20% chord Max camber 4.6% at 30% chord Source UIUC Airfoil Coordinates Database