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.

(as5045-il) AS5045 (15%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil Max thickness 15% at 37.5% chord Max camber 1% at 27.2% chord Max Cl/Cd 30 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n63415-il) NACA 63-415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-415 airfoil Max thickness 15% at 34.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 30 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e403-il) EPPLER 403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E403 general purpose airfoil Max thickness 15% at 37.9% chord Max camber 3.2% at 75.5% chord Max Cl/Cd 29.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n64212ma-il) NACA 64(1)-212 MOD A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil Max thickness 12% at 41.2% chord Max camber 2.5% at 21.5% chord Max Cl/Cd 29.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(curtisc72-il) Curtis C-72		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Curtis C-72 airfoil Max thickness 11.7% at 30% chord Max camber 3.8% at 50% chord Max Cl/Cd 29.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(n64110-il) NACA 64-110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-110 airfoil Max thickness 10% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 29.9 at Re# 50,000 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 29.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e874-il) EPPLER 874 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E874 hydrofoil Max thickness 7.9% at 28.8% chord Max camber 0.9% at 35.7% chord Max Cl/Cd 29.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e186-il) E186 (10.27%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E186 low Reynolds number airfoil Max thickness 10.2% at 29% chord Max camber 0.8% at 29% chord Max Cl/Cd 29.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(doa5-il) DORNIER A-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dornier A-5 airfoil (reconstruction) (DO 228 wing) Max thickness 16.2% at 40.1% chord Max camber 2.5% at 76% chord Max Cl/Cd 29.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database