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.

(goe14k-il) GOE 14K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 14K airfoil Max thickness 12% at 50% chord Max camber 2.7% at 50% chord Max Cl/Cd 25.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe682-il) GOE 682 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 682 airfoil Max thickness 10.7% at 30% chord Max camber 4.3% at 40% chord Max Cl/Cd 25.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rc0864c-il) NASA/LANGLEY RC08-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 08-64C rotorcraft airfoil Max thickness 8% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 25.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae2822-il) RAE 2822 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 2822 transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 25.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae69ck-il) RAE6-9CK AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE6-9CK transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 25.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(sc20714-il) NASA SC(2)-0714 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0714 airfoil (NASA TP-2969) Max thickness 14% at 37% chord Max camber 2.5% at 81% chord Max Cl/Cd 25.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e557-il) EPPLER 557 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E557 general aviation airfoil Max thickness 16% at 30.2% chord Max camber 3.7% at 60.8% chord Max Cl/Cd 25.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah63k127-il) AH 63-K-127/24		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 63-K-127/24 airfoil for use with flaps (K) Max thickness 12.7% at 40.2% chord Max camber 3.8% at 43.5% chord Max Cl/Cd 25.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe627-il) GOE 627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 627 airfoil Max thickness 15.8% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 25.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(prandtl-d-tip-ns) Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider tip airfoil Max thickness 9.6% at 26.8% chord Max camber 0% at 0% chord Max Cl/Cd 25.4 at Re# 50,000 Source NASA