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.

(goe599-il) GOE 599 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 599 airfoil Max thickness 10% at 29.6% chord Max camber 1.5% at 59.7% chord Max Cl/Cd 80.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e837-il) EPPLER E837 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E837 hydrofoil Max thickness 16.1% at 36.9% chord Max camber 0% at 0% chord Max Cl/Cd 80.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20614-il) NASA SC(2)-0614 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0614 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 2.1% at 81% chord Max Cl/Cd 80.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(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 80 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20714-il) NASA SC(2)-0714 AIRFOIL		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 (NASA TP-2969) Max thickness 14% at 37% chord Max camber 2.5% at 81% chord Max Cl/Cd 80 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(giiik-il) GIII BL369 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35% chord Max camber 1.5% at 25% chord Max Cl/Cd 79.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s833-nr) NREL's S833 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S833 primary 18.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.10 Clmax(R)=1.13 High max lift coef Max thickness 18% at 36.3% chord Max camber 2.5% at 78.8% chord Max Cl/Cd 79.9 at Re# 1,000,000 Source NWTC National WInd Technology Center
(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 79.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(l188root-il) LOCKHEED L-188 ROOT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 root airfoil NACA 0014 -1.10 40/1.051 Cli=.3 a=.8 Max thickness 14% at 41.3% chord Max camber 2% at 51.7% chord Max Cl/Cd 79.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(usa31-il) USA 31 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-31 airfoil Max thickness 14.8% at 19.7% chord Max camber 9.3% at 39.7% chord Max Cl/Cd 79.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database