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.

(naca671215-il) NACA 67		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 67 Max thickness 15% at 50% chord Max camber 1.1% at 50% chord Max Cl/Cd 21.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq3518-il) HQ 3.5/18 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/18 R/C sailplane airfoil Max thickness 18% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 21.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e473-il) EPPLER 473 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E473 aerobatic aircraft airfoil Max thickness 16.2% at 21.2% chord Max camber 0% at 0% chord Max Cl/Cd 21.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah85l120-il) AH 85-L-120/17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 85-L-120/17 symmetrical airfoil Max thickness 12.1% at 43.5% chord Max camber 0% at 0% chord Max Cl/Cd 21.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s1010-il) S1010 HPV airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1010 HPV airfoil Max thickness 6% at 23.3% chord Max camber 0% at 0% chord Max Cl/Cd 21.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(e543-il) EPPLER 543 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E543 general aviation airfoil Max thickness 17.2% at 40.7% chord Max camber 1.9% at 31% chord Max Cl/Cd 21.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(b540ols-il) BELL 540 AIRFOIL (MODIFIED NACA 0012)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell AH-1 rotor blade airfoil (operational loads survey) Max thickness 9.7% at 22.1% chord Max camber 0% at 0% chord Max Cl/Cd 21.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh104-il) MH 104 15.28%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 104 for stall controlled wind turbines Max thickness 15.2% at 26.4% chord Max camber 1.9% at 31.1% chord Max Cl/Cd 21.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ht12-il) HT12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT12 airfoil Max thickness 5% at 18.6% chord Max camber 0% at 0% chord Max Cl/Cd 21.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe652-il) GOE 652 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 652 airfoil Max thickness 17.1% at 20% chord Max camber 9.3% at 50% chord Max Cl/Cd 21.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database