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.

(mh43-il) MH 43 8.5%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 43 for F3B and F3E Max thickness 8.5% at 31.4% chord Max camber 1.7% at 36.4% chord Max Cl/Cd 100 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ls421mod-il) NASA/LANGLEY LS(1)-0421MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0421MOD general aviation airfoil Max thickness 21% at 32.5% chord Max camber 2.3% at 30% chord Max Cl/Cd 100 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe177-il) GOE 177 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 177 airfoil Max thickness 7.7% at 20% chord Max camber 5% at 40% chord Max Cl/Cd 99.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s4110-il) S4110		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4110 low Reynolds number airfoil Max thickness 8.4% at 26.6% chord Max camber 3.1% at 45.4% chord Max Cl/Cd 99.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e222-il) E222 (10.17%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E222 low Reynolds number airfoil Max thickness 10.2% at 31.1% chord Max camber 2.1% at 55.3% chord Max Cl/Cd 99.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(hq308-il) HQ 3.0/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 99.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hor20-il) ONERA HOR20 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 20.4% at 24.3% chord Max camber 3.3% at 51.3% chord Max Cl/Cd 99.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e374-il) E374		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E374 low Reynolds number airfoil Max thickness 10.9% at 34.3% chord Max camber 2% at 38.9% chord Max Cl/Cd 99.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(raf34-il) RAF 34 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-34 airfoil Max thickness 12.6% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 99.8 at Re# 1,000,000 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 99.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database