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.

(fx60160-il) FX 60-160 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord Max camber 3.1% at 60% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe122-il) GOE 122 (MVA H.2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 122 (MVA H.2) airfoil Max thickness 7.3% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah88k136-il) AH 88-K-136/16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-136/16 airfoil for use with flaps (K) Max thickness 13.5% at 44.9% chord Max camber 3% at 41.9% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m15-il) NACA M15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-15 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 30% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh32-il) MH 32 8.7%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 32 for F3E and F3B Max thickness 8.7% at 30.2% chord Max camber 2.3% at 45.7% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe276-il) GOE 276 (DAIMLER VII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 276 (DAIMLER VII) airfoil Max thickness 7.3% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq2012-il) HQ 2.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe143-il) GOE 143 (MVA H.20) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 143 (MVA H.20) airfoil Max thickness 7.4% at 19.9% chord Max camber 3.8% at 29.9% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe632-il) GOE 632 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 632 airfoil Max thickness 14% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e556-il) EPPLER 556 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E556 general aviation airfoil Max thickness 16% at 31.1% chord Max camber 3.1% at 61.4% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database