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.

(ah88k130-il) AH 88-K-130/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-130/20 airfoil for use with flaps (K) Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord Max Cl/Cd 147.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(strand-il) STRAND AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Strand high lift airfoil Max thickness 15.4% at 26.1% chord Max camber 4.1% at 32.1% chord Max Cl/Cd 147.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e398-il) EPPLER 398 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E398 human powered aircraft airfoil Max thickness 14.2% at 29.6% chord Max camber 5.3% at 50.9% chord Max Cl/Cd 147 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe804-il) GOE 804 (EA 8) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 804 (EA 8) airfoil Max thickness 6% at 40% chord Max camber 6.3% at 50% chord Max Cl/Cd 147 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e694-il) EPPLER 694 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E694 sailplane airfoil Max thickness 15.4% at 40.4% chord Max camber 4.9% at 59.2% chord Max Cl/Cd 147 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe233-il) GOE 233 (MVA CA4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 233 (MVA CA4) airfoil Max thickness 11.6% at 19.8% chord Max camber 8.2% at 49.8% chord Max Cl/Cd 146.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s1020-il) Ornithopter airfoil.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1020 ornithopter airfoil Max thickness 15.1% at 33.8% chord Max camber 4.6% at 57% chord Max Cl/Cd 146.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe12k-il) GOE 12K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 12K airfoil Max thickness 11.1% at 50% chord Max camber 4.1% at 60% chord Max Cl/Cd 146.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e392-il) E392 (10.15%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E392 low Reynolds number airfoil Max thickness 10.1% at 31.6% chord Max camber 3.7% at 45.3% chord Max Cl/Cd 146.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(gm15sm-il) GM15 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gilbert Morris GM15 F1C class free flight flapper airfoil Max thickness 6.7% at 20.5% chord Max camber 4.8% at 49.3% chord Max Cl/Cd 146.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database