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.

(e520-il) EPPLER 520 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E520 tailplane airfoil Max thickness 15% at 36.7% chord Max camber 0% at 0% chord Max Cl/Cd 62.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(b707d-il) BOEING 707 .54 SPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 707 airfoils Max thickness 9% at 40% chord Max camber 1.8% at 30% chord Max Cl/Cd 62.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(giiif-il) GIII BL145 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 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 62.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(c5d-il) LOCKHEED C-5A BL758.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 60% chord Max Cl/Cd 62.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(c5c-il) LOCKHEED C-5A BL576 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 65% chord Max Cl/Cd 62.3 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 62.3 at Re# 500,000 Source NWTC National WInd Technology Center
(tempest1-il) HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 37.5% semispan airfoil (NPL?) Max thickness 14.5% at 38.3% chord Max camber 1% at 40.4% chord Max Cl/Cd 62.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fg4-il) Fage & Collins 4		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fage & Collins 4 airfoil Max thickness 12.7% at 30% chord Max camber 4.7% at 30% chord Max Cl/Cd 62.2 at Re# 500,000 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 62.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx77w270s-il) FX 77-W-270S		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-270S airfoil for use on wind turbines (W) Max thickness 27.1% at 33.9% chord Max camber 4.2% at 27.9% chord Max Cl/Cd 62.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database