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.

(hs1404-il) HAM-STD HS1-404 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 4% at 18% chord Max camber 3.1% at 46% chord Max Cl/Cd 42.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe81-il) GOE 81 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 81 airfoil Max thickness 7.4% at 29.9% chord Max camber 6.3% at 29.9% chord Max Cl/Cd 42.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe437-il) GOE 437 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 437 airfoil Max thickness 7.1% at 30% chord Max camber 4.8% at 40% chord Max Cl/Cd 42.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe281-il) GOE 281 (DAIMLER XII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 281 (DAIMLER XII) airfoil Max thickness 8% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 42.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq359-il) HQ 3.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 42 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah79100a-il) AH 79-100 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-100A airfoil Max thickness 10% at 27.9% chord Max camber 3.6% at 56.5% chord Max Cl/Cd 41.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe403-il) GOE 403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 403 airfoil Max thickness 6.7% at 29.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 41.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe400-il) GOE 400 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 400 airfoil Max thickness 6.1% at 20% chord Max camber 4.9% at 40% chord Max Cl/Cd 41.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sa7025-il) SA7025		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7025 low Reynolds number airfoil Max thickness 8% at 29.2% chord Max camber 3.6% at 43.2% chord Max Cl/Cd 41.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe373-il) GOE 373 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 373 airfoil Max thickness 6.5% at 29.9% chord Max camber 5.1% at 39.9% chord Max Cl/Cd 41.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database

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