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.

(goe534-il) GOE 534 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 534 airfoil Max thickness 14.1% at 19.6% chord Max camber 5.2% at 39.6% chord Max Cl/Cd 114.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe744-il) GOE 744 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 744 airfoil Max thickness 14.5% at 20% chord Max camber 7% at 30% chord Max Cl/Cd 114.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah93156-il) AH 93-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-156 airfoil Max thickness 15.7% at 39.5% chord Max camber 3.7% at 41.5% chord Max Cl/Cd 114.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe504-il) GOE 504 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 504 airfoil Max thickness 18% at 29.2% chord Max camber 5.4% at 39.2% chord Max Cl/Cd 114.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe133-il) GOE 133 (MVA H.11) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 133 (MVA H.11) airfoil Max thickness 7.9% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 114.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(kc135d-il) KC-135 BL351.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 9% at 40% chord Max camber 1.9% at 30% chord Max Cl/Cd 114.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe550-il) GOE 550 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 550 airfoil Max thickness 13% at 20% chord Max camber 4.3% at 50% chord Max Cl/Cd 114.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m17-il) NACA M17 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-17 airfoil Max thickness 8.1% at 40% chord Max camber 4.1% at 30% chord Max Cl/Cd 114.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(clarky-il) CLARK Y AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK Y airfoil Max thickness 11.7% at 28% chord Max camber 3.4% at 42% chord Max Cl/Cd 114.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe478-il) GOE 478 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 478 airfoil Max thickness 13.4% at 29.6% chord Max camber 4.3% at 39.6% chord Max Cl/Cd 114.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database