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.

(e226-il) E226 (10.19%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E226 low Reynolds number airfoil Max thickness 10.2% at 31.3% chord Max camber 0.5% at 56.9% chord Max Cl/Cd 59.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e1212-il) EPPLER E1212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1212 general aviation airfoil Max thickness 17.7% at 23.4% chord Max camber 3.2% at 36.4% chord Max Cl/Cd 59.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord Max camber 1.4% at 30% chord Max Cl/Cd 59.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s102s-il) SOMERS S102 AIRFOIL (SHARP)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2.1% at 68.7% chord Max Cl/Cd 59.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(c141e-il) LOCKHEED C-141 BL761.11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.5% at 40.2% chord Max camber 1.8% at 50% chord Max Cl/Cd 59.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(oa212-il) ONERA OA212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12% at 31.8% chord Max camber 2.3% at 31.8% chord Max Cl/Cd 59.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(as5045-il) AS5045 (15%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil Max thickness 15% at 37.5% chord Max camber 1% at 27.2% chord Max Cl/Cd 59.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag455ct02r-il) AG455ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG455ct -02f airfoil Max thickness 6.5% at 23.3% chord Max camber 1.8% at 33.1% chord Max Cl/Cd 59.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh64-il) MH 64 8.59%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 64 for flying wings Max thickness 8.6% at 26.9% chord Max camber 1.4% at 41.8% chord Max Cl/Cd 59.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh33-il) MH33		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 33 for F3E and F3B Max thickness 7.3% at 29.3% chord Max camber 1.1% at 43.9% chord Max Cl/Cd 59.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database