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.

(naca1412-il) NACA 1412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1412 airfoil Max thickness 12% at 29.9% chord Max camber 1% at 40% chord Max Cl/Cd 66 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s821-nr) NREL's S821 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S821 root 24.0% Dia=10 to 20 m Re=8.0E+5 Clmax(S)=1.40 Clmax(R)=1.35 Restrained max lift coef Max thickness 24.2% at 24.6% chord Max camber 2.6% at 77.6% chord Max Cl/Cd 66 at Re# 500,000 Source NWTC National WInd Technology Center
(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0714 airfoil (Ref. NASA TP-2890) Max thickness 13.9% at 37% chord Max camber 2.5% at 80% chord Max Cl/Cd 66 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 65.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(joukowsk-il) 12% JOUKOWSKI AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	12% Joukowski airfoil Max thickness 11.8% at 25% chord Max camber 0% at 9.5% chord Max Cl/Cd 65.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(rae5213-il) RAE(NPL) 5213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE(NPL) 5213 transonic airfoil Max thickness 10% at 35.5% chord Max camber 1.4% at 69.1% chord Max Cl/Cd 65.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ht23-il) HT23		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT23 airfoil Max thickness 6.5% at 20.8% chord Max camber 1.1% at 22.6% chord Max Cl/Cd 65.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(trainer60-il) TRAINER60		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Planes R/C Trainer 60 airfoil Max thickness 18.3% at 27.1% chord Max camber 0.1% at 1.3% chord Max Cl/Cd 65.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca0018-il) NACA 0018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 65.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rc10b3-il) NASA/LANGLEY RC-10(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-10(B)3 rotorcraft airfoil Max thickness 10% at 37.7% chord Max camber 1.7% at 30.3% chord Max Cl/Cd 65.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database