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.

(arad13-il) ARA-D 13% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 13% thick propeller airfoil Max thickness 13% at 25% chord Max camber 3.6% at 30% chord Source UIUC Airfoil Coordinates Database
(arad20-il) ARA-D 20% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 20% thick propeller airfoil Max thickness 20% at 25% chord Max camber 3.8% at 25% chord Source UIUC Airfoil Coordinates Database
(arad6-il) ARA-D 6% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 6% thick propeller airfoil Max thickness 6% at 20% chord Max camber 5% at 45% chord 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 Source UIUC Airfoil Coordinates Database
(as5046-il) AS5046 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5046 airfoil Ashok Gopalarathnam/Selig 16% airfoil Max thickness 16% at 37.6% chord Max camber 0.7% at 77.4% chord Source UIUC Airfoil Coordinates Database

(as5048-il) AS5048 (18%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil Max thickness 18% at 38.3% chord Max camber 0.8% at 77.8% chord Source UIUC Airfoil Coordinates Database
(atr72sm-il) Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ATR 72 wing airfoil (from NTSB report) Max thickness 14.5% at 25.4% chord Max camber 2.9% at 21.4% chord Source UIUC Airfoil Coordinates Database
(august160-il) AUGUST 160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AUGUST 160 airfoil Max thickness 16% at 25% chord Max camber 5.4% at 25% chord Source UIUC Airfoil Coordinates Database
(avistar-il) AVISTAR		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hobbico R/C Avistar trainer airfoil Max thickness 14.5% at 34.2% chord Max camber 2.3% at 37.9% chord Source UIUC Airfoil Coordinates Database
(b29root-il) B-29 ROOT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing B-29 root airfoil Max thickness 22% at 30.2% chord Max camber 1.7% at 30.2% chord Source UIUC Airfoil Coordinates Database