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.

(hq159b-il) HQ 1.5/9 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/9 B R/C sailplane airfoil Max thickness 9% at 37.1% chord Max camber 1.5% at 50% chord Max Cl/Cd 49.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(df102-il) DF102		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	David Fraser DF 102 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.4% at 43.5% chord Max Cl/Cd 49.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m12-il) NACA M12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 49 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e851-il) EPPLER E851 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E851 propeller airfoil Max thickness 9% at 37% chord Max camber 2.3% at 66.3% chord Max Cl/Cd 49 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe655-il) GOE 655 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 655 airfoil Max thickness 13.9% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 49 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe11k-il) GOE 11K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 11K airfoil Max thickness 7.5% at 50% chord Max camber 2.7% at 60% chord Max Cl/Cd 49 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq158-il) HQ 1.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/8 R/C sailplane airfoil Max thickness 8% at 32.5% chord Max camber 1.5% at 50% chord Max Cl/Cd 49 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mb253515sm-il) MB253515 15.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Mike Bame MB253515 low Reynolds number airfoil Max thickness 15% at 35% chord Max camber 2.5% at 37.5% chord Max Cl/Cd 49 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe241-il) GOE 241 (MVA PR.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 241 (MVA PR.1) airfoil Max thickness 18.9% at 29.5% chord Max camber 8.4% at 49.5% chord Max Cl/Cd 49 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rc10n1-il) NASA/LANGLEY RC-10(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-10(N)1 rotorcraft airfoil Max thickness 10% at 37.6% chord Max camber 1.5% at 25% chord Max Cl/Cd 49 at Re# 100,000 Source UIUC Airfoil Coordinates Database