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.

(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 66.3 at Re# 100,000 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 66.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e818-il) EPPLER 818 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E818 hydrofoil Max thickness 9.4% at 33.1% chord Max camber 2.8% at 67% chord Max Cl/Cd 66.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx63110-il) FX 63-110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-110 airfoil Max thickness 11% at 30.8% chord Max camber 4.3% at 50% chord Max Cl/Cd 66.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s1210-il) S1210 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1210 high lift low Reynolds number airfoil Max thickness 12% at 21.4% chord Max camber 6.7% at 51.1% chord Max Cl/Cd 66 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ah79100b-il) AH 79-100 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-100B airfoil Max thickness 10% at 30.9% chord Max camber 6.4% at 50% chord Max Cl/Cd 65.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe123-il) GOE 123 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 123 airfoil Max thickness 5.4% at 25% chord Max camber 5.7% at 40% chord Max Cl/Cd 65.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(oaf095-il) OAF095 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF095 Fenestron airfoil Max thickness 9.5% at 23.2% chord Max camber 3.9% at 53.1% chord Max Cl/Cd 65.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe500-il) GOE 500 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 500 airfoil Max thickness 10% at 30% chord Max camber 6% at 50% chord Max Cl/Cd 65.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sg6043-il) SG6043		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6043 wind turbine airfoil (high L/D) Max thickness 10% at 32.1% chord Max camber 5.1% at 53.3% chord Max Cl/Cd 65.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database