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.

(mh84-il) MH 84 13.69%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 84 for flying wings (hang glider) Max thickness 13.7% at 21.5% chord Max camber 4.1% at 36.6% chord Max Cl/Cd 66.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa45m-il) USA 45 M AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-45M airfoil Max thickness 11.6% at 30% chord Max camber 3.3% at 30% chord Max Cl/Cd 66.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx05h126-il) WORTMANN FX 05-H-126 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 05-H-126 rotorcraft airfoil Max thickness 12.6% at 37.1% chord Max camber 4.4% at 37.1% chord Max Cl/Cd 66.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe629-il) GOE 629 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 629 airfoil Max thickness 13.6% at 29.4% chord Max camber 2.8% at 39.4% chord Max Cl/Cd 66.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah93157-il) AH 93-157		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-157 airfoil Max thickness 15.7% at 39.6% chord Max camber 3.5% at 41.7% chord Max Cl/Cd 66.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(clarym15-il) CLARK YM-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YM15 airfoil Max thickness 15% at 29.6% chord Max camber 3.6% at 39.6% chord Max Cl/Cd 66.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe633-il) GOE 633 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 633 airfoil Max thickness 13.8% at 19.7% chord Max camber 4% at 39.7% chord Max Cl/Cd 66.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx69h083-il) BELL/WORTMANN FX 69-H-083 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/Wortmann FX 69-H-083 rotorcraft airfoil Max thickness 8.4% at 33.3% chord Max camber 2.5% at 33.3% chord Max Cl/Cd 66.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(arad10-il) ARA-D 10% 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 10% thick propeller airfoil Max thickness 10% at 25% chord Max camber 4% at 35% chord Max Cl/Cd 66.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe12k-il) GOE 12K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 12K airfoil Max thickness 11.1% at 50% chord Max camber 4.1% at 60% chord Max Cl/Cd 66.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database