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.

(e1230-il) EPPLER 1230 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1230 general aviation airfoil (Long-EZ and Defiant wing airfoil) Max thickness 17.4% at 30.9% chord Max camber 3.6% at 25.6% chord Max Cl/Cd 24.9 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 24.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca0006-il) NACA 0006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0006 airfoil Max thickness 6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 24.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(k3-il) GRUMMAN K-3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman K-3 transonic airfoil (GAC .70-.83-17.5) Max thickness 17.3% at 33.1% chord Max camber 2.6% at 74.7% chord Max Cl/Cd 24.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca65209-il) NACA 65-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 24.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(naca632615-il) NACA 63(2)-615		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-615 airfoil Max thickness 15% at 34.8% chord Max camber 3.3% at 50% chord Max Cl/Cd 24.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh92-il) MH 92 15.49%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 92 parafoil Max thickness 15.5% at 27.4% chord Max camber 1.4% at 15.1% chord Max Cl/Cd 24.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sc20712-il) NASA SC(2)-0712 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0712 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 2.2% at 81% chord Max Cl/Cd 24.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe526-il) GOE 526 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 526 airfoil Max thickness 12.3% at 29.7% chord Max camber 4.1% at 39.7% chord Max Cl/Cd 24.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca23021-il) NACA 23021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23021 airfoil Max thickness 21% at 30% chord Max camber 1.9% at 10% chord Max Cl/Cd 24.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database