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.

(goe414-il) GOE 414 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 414 airfoil Max thickness 13.6% at 29.7% chord Max camber 5.3% at 39.7% chord Max Cl/Cd 124.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca643618-il) NACA 64(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord Max camber 3.3% at 50% chord Max Cl/Cd 124.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(2032c-il) 20-32C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dillner 20-32-C low Reynolds number airfoil Max thickness 8% at 20% chord Max camber 6.9% at 40% chord Max Cl/Cd 124.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(defcnd1-il) DEFIANT CANARD BL20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL20 airfoil Max thickness 20.9% at 28.6% chord Max camber 4.5% at 36.1% chord Max Cl/Cd 124.9 at Re# 1,000,000 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 124.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(a18-il) A18 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Archer A18 F1C free flight airfoil(original) Max thickness 7.3% at 30% chord Max camber 3.9% at 45% chord Max Cl/Cd 124.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq3011-il) HQ 3.0/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/11 R/C sailplane airfoil Max thickness 11% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 124.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e207-il) E207 (12.04%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E207 low Reynolds number airfoil Max thickness 12% at 29.6% chord Max camber 2.5% at 38.6% chord Max Cl/Cd 124.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe546-il) GOE 546 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 546 airfoil Max thickness 10.4% at 30% chord Max camber 3.6% at 50% chord Max Cl/Cd 124.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe173-il) GOE 173 (ALBATROS 6020) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 173 (Albatros 6020) airfoil Max thickness 7.8% at 20% chord Max camber 5.9% at 40% chord Max Cl/Cd 124.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database