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.

(e520-il) EPPLER 520 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E520 tailplane airfoil Max thickness 15% at 36.7% chord Max camber 0% at 0% chord Max Cl/Cd 67.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ea81006-il) EPPLER EA 8(-1)-006 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 8(-1)-006 airfoil Max thickness 6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 67.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hsnlf213-il) HSNLF(1)-0213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley HSNLF(1)-0213 high speed natural laminar flow airfoil Max thickness 13.3% at 42.4% chord Max camber 1.4% at 32.4% chord Max Cl/Cd 67.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe388-il) GOE 388 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 388 airfoil Max thickness 10.2% at 29.9% chord Max camber 5.4% at 39.9% chord Max Cl/Cd 67.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca66210-il) NACA 66-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 67.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(nlr7301-il) NLR-7301 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7301 transonic airfoil Max thickness 16.5% at 35% chord Max camber 1.7% at 75% chord Max Cl/Cd 67.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e836-il) EPPLER E836 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E836 hydrofoil Max thickness 12.6% at 42.8% chord Max camber 0% at 0% chord Max Cl/Cd 67.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e184-il) E184 (8.33%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E184 low Reynolds number airfoil Max thickness 8.3% at 33.3% chord Max camber 0.8% at 38.3% chord Max Cl/Cd 67 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(b707b-il) BOEING 707 .19 SPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 707 airfoils Max thickness 12.1% at 29.9% chord Max camber 0.7% at 9.9% chord Max Cl/Cd 67 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ultimate-il) ULTIMATE		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Carl Goldberg R/C Ultimate Bipe airfoil Max thickness 12.8% at 34.2% chord Max camber 0% at 0% chord Max Cl/Cd 67 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database