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.

(fx66h60-il) FX 66-H-60		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-60 airfoil Max thickness 6% at 22.2% chord Max camber 1.7% at 17% chord Max Cl/Cd 28.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e228-il) E10(08%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E228 low Reynolds number airfoil Max thickness 10.1% at 31.9% chord Max camber 0.3% at 31.9% chord Max Cl/Cd 28.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n63215-il) NACA 63-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 28.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nl722362-il) NLR-7223-62 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7223-62 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 21.6% chord Max Cl/Cd 28.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae5215-il) RAE 5215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 5215 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.5% at 69.1% chord Max Cl/Cd 28.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(n63015a-il) NACA 63-015A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-015A airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord Max Cl/Cd 28.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s3010-il) S3010-103-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3010 low Reynolds number airfoil Max thickness 10.3% at 25% chord Max camber 2.3% at 43.3% chord Max Cl/Cd 28.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe654-il) GOE 654 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 654 airfoil Max thickness 14.5% at 30% chord Max camber 5.2% at 40% chord Max Cl/Cd 28.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ys930-il) YS-930		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	YS930 hydrofoil (Shen / Eppler) Max thickness 9.1% at 35% chord Max camber 2.9% at 59.2% chord Max Cl/Cd 28.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s3-il) REPUBLIC S-3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Republic S-3 airfoil (P-47 wing airfoil) Max thickness 11% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 28.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database