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.

(goe117-il) GOE 117 (MVA MK.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 117 (MVA MK.4) airfoil Max thickness 9% at 29.8% chord Max camber 4.6% at 39.8% chord Max Cl/Cd 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe600-il) GOE 600 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 600 airfoil Max thickness 13.1% at 29.4% chord Max camber 1.9% at 49.4% chord Max Cl/Cd 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(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 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(tsagi8-il) TSAGI 8% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 8% airfoil Max thickness 8% at 30% chord Max camber 1.3% at 30% chord Max Cl/Cd 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe575-il) GOE 575 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 575 airfoil Max thickness 13.3% at 29.8% chord Max camber 3.6% at 39.8% chord Max Cl/Cd 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(glennmartin3-il) Glenn Martin 3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 3 airfoil Max thickness 13.8% at 30% chord Max camber 4.6% at 30% chord Max Cl/Cd 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(cr1-il) CURTISS CR-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Curtiss CR-1 general aviation airfoil Max thickness 12.2% at 24% chord Max camber 4.7% at 42% chord Max Cl/Cd 32.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe114-il) GOE 114 (MVA MK.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 114 (MVA MK.1) airfoil Max thickness 9.6% at 29.7% chord Max camber 3.5% at 49.7% chord Max Cl/Cd 32.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq1010-il) HQ 1.0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 32.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(giiig-il) GIII BL167 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 32.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database