Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(sd7032-il) SD7032-099-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7032 low Reynolds number airfoil Max thickness 10% at 26.6% chord Max camber 3.4% at 45.1% chord Max Cl/Cd 114.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mrc-20-il) MRC-20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela MRC-20 Max thickness 15.6% at 38.2% chord Max camber 2.9% at 48% chord Max Cl/Cd 114.5 at Re# 1,000,000 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 114.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e343-il) EPPLER 343 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E343 flying wing airfoil Max thickness 14.5% at 30.9% chord Max camber 4% at 26% chord Max Cl/Cd 114.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca65410-il) NACA 65-410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-410 airfoil Max thickness 10% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 114.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(e853-il) EPPLER E853 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E853 propeller airfoil Max thickness 11.6% at 37.1% chord Max camber 3.1% at 56.1% chord Max Cl/Cd 114.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s3025-il) S3025 9.38%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3025 low Reynolds number airfoil Max thickness 9.4% at 30.9% chord Max camber 3% at 44.9% chord Max Cl/Cd 114.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe406-il) GOE 406 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 406 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.5% at 39.9% chord Max Cl/Cd 114.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe322-il) GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 322 (Hansa-Brandenburg IV.1) airfoil Max thickness 13.1% at 29.8% chord Max camber 6% at 29.8% chord Max Cl/Cd 114.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe387-il) GOE 387 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 387 airfoil Max thickness 14.9% at 30% chord Max camber 5.5% at 40% chord Max Cl/Cd 114.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database