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.

(l1003-il) LIEBECK L1003 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Liebeck high lift airfoil Max thickness 17.7% at 30% chord Max camber 6.5% at 30% chord Max Cl/Cd 68.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca0024-il) NACA 0024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0024 airfoil Max thickness 24% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 68.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(doa5-il) DORNIER A-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dornier A-5 airfoil (reconstruction) (DO 228 wing) Max thickness 16.2% at 40.1% chord Max camber 2.5% at 76% chord Max Cl/Cd 68.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e171-il) (Dicke 12.28%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E171 low Reynolds number airfoil Max thickness 12.3% at 32.4% chord Max camber 0% at 0% chord Max Cl/Cd 68.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(tempest1-il) HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 37.5% semispan airfoil (NPL?) Max thickness 14.5% at 38.3% chord Max camber 1% at 40.4% chord Max Cl/Cd 68.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(e171-il) (Dicke 12.28%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E171 low Reynolds number airfoil Max thickness 12.3% at 32.4% chord Max camber 0% at 0% chord Max Cl/Cd 68.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah81k144wfklappe-il) AH 81-K-144 W-F KLAPPE		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 81-K-144 W-F KLAPPE airfoil for use with flaps (K) Max thickness 22% at 17% chord Max camber 1.1% at 56.5% chord Max Cl/Cd 68.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hor04-il) ONERA HOR04 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 4.1% at 33.2% chord Max camber 1.4% at 38.3% chord Max Cl/Cd 68.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(p51dtip-il) P-51D TIP (BL215) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord Max Cl/Cd 68.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca64206-il) NACA 64-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 68.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database