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.

(ht22-il) HT22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT22 airfoil Max thickness 5.1% at 19.1% chord Max camber 1.1% at 22.7% chord Max Cl/Cd 63.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(tempest3-il) HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 96.77% semispan airfoil (NPL?) Max thickness 10% at 38.7% chord Max camber 1% at 40.7% chord Max Cl/Cd 63.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fxl142k-il) FX LIII-142 K 25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX LIII-142 K 25 airfoil Max thickness 14.2% at 30.9% chord Max camber 0% at 0% chord Max Cl/Cd 63.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sd8020-il) SD8020-010-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD8020 low Reynolds number airfoil Max thickness 10.1% at 27.5% chord Max camber 0% at 42.1% chord Max Cl/Cd 63.1 at Re# 500,000 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 63.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(sc20412-il) NASA SC(2)-0412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0412 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.3% at 83% chord Max Cl/Cd 63 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s829-nr) NREL's S829 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S829 tip 16.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=0.70 Clmax(R)=0.68 Restrained max lift coef Max thickness 16% at 48.3% chord Max camber 0.7% at 48.3% chord Max Cl/Cd 63 at Re# 500,000 Source NWTC National WInd Technology Center
(fx83w227-il) FX 83-W-227		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 83-W-227 airfoil for use on wind turbines (W) Max thickness 22.6% at 33.9% chord Max camber 3.4% at 40.2% chord Max Cl/Cd 62.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx76100-il) WORTMANN FX 76-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-100 symmetrical airfoil Max thickness 10.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 62.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(glennmartin4-il) Glenn Martin 4		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 4 airfoil Max thickness 15.5% at 30% chord Max camber 6% at 30% chord Max Cl/Cd 62.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database