Airfoil Tools
Search 1638 airfoils

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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.

(e58-il) EPPLER 58 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E58 low Reynolds number airfoil Max thickness 5.6% at 30% chord Max camber 6.5% at 50% chord Max Cl/Cd 46.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s1091-il) S1091		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1091 airfoil Max thickness 5.1% at 13.4% chord Max camber 5.7% at 45.1% chord Max Cl/Cd 46.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(gm15sm-il) GM15 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gilbert Morris GM15 F1C class free flight flapper airfoil Max thickness 6.7% at 20.5% chord Max camber 4.8% at 49.3% chord Max Cl/Cd 46.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(bw3-il) Bergey BW-3 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bergey BW-3 wind turbine airfoil (smoothed) Max thickness 5% at 7.4% chord Max camber 5.7% at 45.4% chord Max Cl/Cd 46 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(arad6-il) ARA-D 6% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 6% thick propeller airfoil Max thickness 6% at 20% chord Max camber 5% at 45% chord Max Cl/Cd 46 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe427-il) GOE 427 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 427 airfoil Max thickness 4.6% at 20% chord Max camber 5.4% at 40% chord Max Cl/Cd 45.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(arad6-il) ARA-D 6% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 6% thick propeller airfoil Max thickness 6% at 20% chord Max camber 5% at 45% chord Max Cl/Cd 45.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(davissm-il) davissm		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Davis 3R F1B free flight airfoil (smoothed) Max thickness 5.9% at 30.6% chord Max camber 5.9% at 45.4% chord Max Cl/Cd 45.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hs1606-il) HAM-STD HS1-606 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 6% at 18% chord Max camber 4.4% at 46% chord Max Cl/Cd 45.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe494-il) GOE 494 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 494 airfoil Max thickness 5% at 20% chord Max camber 5.1% at 50% chord Max Cl/Cd 45.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database