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.

(stcyr24-il) St. CYR 24 (Bartel 35-IIIC)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 24 (Bartel 35-IIIC) airfoil Max thickness 12.4% at 30% chord Max camber 5.9% at 40% chord Max Cl/Cd 31.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(waspsm-il) WASP (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Mike Fox WASP low Reynolds number airfoil Max thickness 9.4% at 27.1% chord Max camber 3% at 37.9% chord Max Cl/Cd 31.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(oaf128-il) OAF128 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF128 Fenestron airfoil Max thickness 12.8% at 23.2% chord Max camber 1% at 43.7% chord Max Cl/Cd 31.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e560-il) EPPLER 560 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E560 general aviation airfoil Max thickness 16.1% at 24% chord Max camber 4.9% at 51.1% chord Max Cl/Cd 31.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n64212-il) NACA 64(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 31.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe416a-il) GOE 416A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 416A airfoil Max thickness 11.7% at 29.5% chord Max camber 1.3% at 59.6% chord Max Cl/Cd 31.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(kc135b-il) KC-135 BL124.32 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 13% at 40% chord Max camber 1.4% at 20% chord Max Cl/Cd 31.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(avistar-il) AVISTAR		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hobbico R/C Avistar trainer airfoil Max thickness 14.5% at 34.2% chord Max camber 2.3% at 37.9% chord Max Cl/Cd 31.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s1221-flap-il) S1221 w/ 4 deg flap		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord Max camber 5.3% at 52.9% chord Max Cl/Cd 31 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e395-il) EPPLER 395 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E395 human e664ered aircraft airfoil Max thickness 12.3% at 29.5% chord Max camber 5.2% at 52.3% chord Max Cl/Cd 31 at Re# 50,000 Source UIUC Airfoil Coordinates Database