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.

(v13006-il) BOEING VERTOL V13006-.7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V13006-.7 rotorcraft airfoil Max thickness 6% at 30.2% chord Max camber 0.9% at 20.2% chord Max Cl/Cd 46.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(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 46.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ebambino7-il) E. Bambino		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	E. Bambino airfoil Max thickness 6% at 40% chord Max camber 1.9% at 20% chord Max Cl/Cd 46.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(marske3-il) MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IID root airfoil (NACA 43012A/24112 hybrid) Max thickness 12.1% at 30% chord Max camber 2.8% at 15% chord Max Cl/Cd 46.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(dfvlrr4-il) DFVLR R-4 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	DFVLR R-4 transonic airfoil Max thickness 13.4% at 37.9% chord Max camber 2.1% at 79.9% chord Max Cl/Cd 46.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(hq09-il) HQ 0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/9 R/C sailplane airfoil Max thickness 8.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 46.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx78k150-il) FX 78-K-150/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 78-K-150/20 airfoil for use with flaps (K) Max thickness 15.1% at 43.5% chord Max camber 4.3% at 43.5% chord Max Cl/Cd 46.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e475-il) E475 (15.01%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E475 aerobatic aircraft airfoil Max thickness 15% at 21.7% chord Max camber 0% at 0% chord Max Cl/Cd 46.2 at Re# 200,000 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 46.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20606-il) NASA SC(2)-0606 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0606 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.3% at 81% chord Max Cl/Cd 46.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database