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.

(mh94-il) MH 94 16.03%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 94 parafoil Max thickness 16% at 34.1% chord Max camber 1.3% at 74.1% chord Max Cl/Cd 40.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(vr14-il) BOEING-VERTOL VR-14 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-14 rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.7% at 20% chord Max Cl/Cd 40.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(pw75-pw) PW75		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Modified PW51 with some more reflex Max thickness 8.9% at 27.5% chord Max camber 1.5% at 23.4% chord Max Cl/Cd 40.3 at Re# 100,000 Source RC Groups
(raf69-il) RAF 69 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-69 airfoil Max thickness 20.6% at 30% chord Max camber 1.7% at 50% chord Max Cl/Cd 40.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ah93k131-il) AH 93-K-131/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-131/15 airfoil for use with flaps (K) Max thickness 13.1% at 41.3% chord Max camber 3.6% at 41.3% chord Max Cl/Cd 40.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(hor04-il) ONERA HOR04 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 4.1% at 33.2% chord Max camber 1.4% at 38.3% chord Max Cl/Cd 40.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rae5214-il) RAE 5214 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 5214 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.4% at 69.1% chord Max Cl/Cd 40.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(eh1070-il) Eh 1.0/7.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord Max camber 1% at 25.9% chord Max Cl/Cd 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx68h120-il) FX 68-H-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 68-H-120 airfoil Max thickness 11.8% at 25% chord Max camber 2.3% at 33.9% chord Max Cl/Cd 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ah94156-il) AH 94-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-156 airfoil Max thickness 15.6% at 39.6% chord Max camber 3.6% at 41.5% chord Max Cl/Cd 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database