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.

(hq2590sm-il) HQ 2.5/9.0 smoothed by Eppler		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/9 R/C sailplane airfoil (smoothed) Max thickness 9% at 35% chord Max camber 2.5% at 55% chord Max Cl/Cd 58.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe362-il) GOE 362 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 362 airfoil Max thickness 6.6% at 20% chord Max camber 5.3% at 40% chord Max Cl/Cd 58.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe117-il) GOE 117 (MVA MK.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 117 (MVA MK.4) airfoil Max thickness 9% at 29.8% chord Max camber 4.6% at 39.8% chord Max Cl/Cd 58.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hs1712-il) HAM-STD HS1-712 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 12% at 36% chord Max camber 4.9% at 44% chord Max Cl/Cd 58.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe391-il) GOE 391 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 391 airfoil Max thickness 5.1% at 40% chord Max camber 3.2% at 40% chord Max Cl/Cd 58.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe279-il) GOE 279 (DAIMLER X) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 279 (DAIMLER X) airfoil Max thickness 7.4% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 58.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe408-il) GOE 408 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 408 airfoil Max thickness 7.8% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 58.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe310-il) GOE 310 (MVA H.42) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 310 (MVA H.42) airfoil Max thickness 8.1% at 29.9% chord Max camber 4.8% at 39.9% chord Max Cl/Cd 58.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe303-il) GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 303 (Friedrichshafen G03) airfoil Max thickness 9.8% at 29.9% chord Max camber 5.9% at 39.9% chord Max Cl/Cd 58.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe177-il) GOE 177 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 177 airfoil Max thickness 7.7% at 20% chord Max camber 5% at 40% chord Max Cl/Cd 58.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database