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.

(e201-il) E201 (11.88%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E201 low Reynolds number airfoil Max thickness 11.9% at 30.8% chord Max camber 2.6% at 49.4% chord Max Cl/Cd 122.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq17-il) HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Airfoil measured from an ASW22 wing Max thickness 15.2% at 42% chord Max camber 4.5% at 42% chord Max Cl/Cd 122.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe741-il) GOE 741 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 741 airfoil Max thickness 15.3% at 30% chord Max camber 4.8% at 30% chord Max Cl/Cd 122.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(clarkx-il) CLARK X AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK X airfoil Max thickness 11.7% at 30% chord Max camber 3.3% at 40% chord Max Cl/Cd 122.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(r1082t-il) RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082T Voyager tip outer aft wing airfoil Max thickness 16% at 40% chord Max camber 3% at 40% chord Max Cl/Cd 122.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(sa7024-il) SA7024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7024 low Reynolds number airfoil Max thickness 7% at 25.9% chord Max camber 3.3% at 43.3% chord Max Cl/Cd 122.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe11k-il) GOE 11K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 11K airfoil Max thickness 7.5% at 50% chord Max camber 2.7% at 60% chord Max Cl/Cd 122.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(usa35-il) USA 35 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35 airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 122.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(davis-corrected-il) DAVIS BASIC B-24 WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Davis basic B-24 wing airfoil Max thickness 15.9% at 29.6% chord Max camber 2.5% at 29.6% chord Max Cl/Cd 122.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe173-il) GOE 173 (ALBATROS 6020) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 173 (Albatros 6020) airfoil Max thickness 7.8% at 20% chord Max camber 5.9% at 40% chord Max Cl/Cd 122.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database