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.

(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 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe514-il) GOE 514 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 514 airfoil Max thickness 16.6% at 19.7% chord Max camber 6.4% at 39.7% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ah82150a-il) AH 82-150 A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(giiin-il) GIII BL450 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 8.4% at 30.2% chord Max camber 2.1% at 20.2% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ah93w145-il) AH 93-W-145		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-145 airfoil for use on wind turbines (W) Max thickness 14.5% at 33.9% chord Max camber 3.9% at 37.1% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx60157-il) FX 60-157 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-157 airfoil Max thickness 15.7% at 40.2% chord Max camber 2.7% at 75% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(oa213-il) ONERA OA213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12.6% at 32.5% chord Max camber 3.3% at 25% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag47ct02r-il) AG47ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG47ct -02f airfoil Max thickness 5% at 22.5% chord Max camber 1.2% at 33.4% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(npl9660-il) NPL 9660 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9660 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database