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.

(e479-il) EPPLER 479 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E479 aerobatic aircraft airfoil Max thickness 16.6% at 25.7% chord Max camber 0% at 0% chord Max Cl/Cd 52.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa49-il) USA 49 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-49 airfoil Max thickness 7.3% at 30% chord Max camber 1.7% at 30% chord Max Cl/Cd 52.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag47ct02r-il) AG47ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG47ct -02f airfoil Max thickness 5% at 22.5% chord Max camber 1.2% at 33.4% chord Max Cl/Cd 52.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s8035-il) S8035 for RC aerobatic 14% thick		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8035 low Reynolds number airfoil Max thickness 14% at 29.1% chord Max camber 0% at 0% chord Max Cl/Cd 52 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(nlr1t-il) NLR-1T AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/NASA/NLR NLR-1T rotorcraft airfoil Max thickness 8.7% at 38.3% chord Max camber 1.3% at 22.3% chord Max Cl/Cd 52 at Re# 200,000 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 52 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(vr15-il) BOEING-VERTOL VR-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/Dadone VR-15 transonic rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.3% at 20% chord Max Cl/Cd 52 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(eiffel371-il) Eiffel 371 (Monge)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 371 (Monge) airfoil Max thickness 14.4% at 30% chord Max camber 3.3% at 30% chord Max Cl/Cd 52 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh81-il) MH 81 13%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 81 for flying wings (hang glider) Max thickness 12.9% at 25.4% chord Max camber 3.3% at 25.4% chord Max Cl/Cd 52 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(arad20-il) ARA-D 20% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 20% thick propeller airfoil Max thickness 20% at 25% chord Max camber 3.8% at 25% chord Max Cl/Cd 52 at Re# 200,000 Source UIUC Airfoil Coordinates Database