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.

(goe184-il) GOE 184 (MVA H.29) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 184 (MVA H.29) airfoil Max thickness 8.3% at 19.9% chord Max camber 5.3% at 39.9% chord Max Cl/Cd 111.9 at Re# 1,000,000 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 111.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(isa962-il) I.S.A. 962		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 962 airfoil Max thickness 9.6% at 20% chord Max camber 4.6% at 40% chord Max Cl/Cd 111.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq3015-il) HQ 3.0/15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/15 R/C sailplane airfoil Max thickness 15% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 111.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(eh2510-il) EH 2.5/10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.5/10 for tailless R/C aircraft Max thickness 10% at 30% chord Max camber 2.5% at 25% chord Max Cl/Cd 111.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe383-il) GOE 383 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 383 airfoil Max thickness 20.2% at 28.7% chord Max camber 5% at 38.7% chord Max Cl/Cd 111.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e547-il) EPPLER 547 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E547 general aviation airfoil Max thickness 17.4% at 40.3% chord Max camber 2% at 30.7% chord Max Cl/Cd 111.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah79k135-il) AH 79-K-135/20 B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-135/20 airfoil for use with flaps (K) Max thickness 13.5% at 40.2% chord Max camber 3.1% at 40.2% chord Max Cl/Cd 111.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe342-il) GOE 342 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 342 airfoil Max thickness 5.4% at 20% chord Max camber 6.2% at 40% chord Max Cl/Cd 111.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe10k-il) GOE 10K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 10K airfoil Max thickness 3.9% at 50% chord Max camber 1.4% at 60% chord Max Cl/Cd 111.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database