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.

(raf31-il) RAF 31 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-31 airfoil Max thickness 12.7% at 30% chord Max camber 2.1% at 50% chord Max Cl/Cd 79.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(eh2070-il) EH 2.0/7.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord Max camber 2% at 25.9% chord Max Cl/Cd 79.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq109-il) HQ 1.0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 79.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf28-il) RAF 28 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-28 airfoil Max thickness 9.8% at 30% chord Max camber 1.9% at 40% chord Max Cl/Cd 79.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s815-nr) NREL's S815 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef Max thickness 26.2% at 25.7% chord Max camber 2.9% at 77.9% chord Max Cl/Cd 79.5 at Re# 500,000 Source NWTC National WInd Technology Center

(goe244-il) GOE 244 (MVA PR.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 244 (MVA PR.4) airfoil Max thickness 17.7% at 19.6% chord Max camber 10% at 49.6% chord Max Cl/Cd 79.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh24-il) MH 24 9.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 24 for F3D Pylon Racing (extended laminar flow) Max thickness 9% at 37.3% chord Max camber 1.2% at 37.3% chord Max Cl/Cd 79.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq2012-il) HQ 2.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 79.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 79.5 at Re# 500,000 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 79.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database