Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(e396-il) EPPLER 396 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E396 human powered aircraft airfoil Max thickness 13.1% at 29.5% chord Max camber 5.4% at 52.1% chord Max Cl/Cd 169.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(uag8814320-il) UAG 88-143/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	UAG 88-143/20 airfoil Max thickness 14.3% at 43.5% chord Max camber 6.2% at 46.7% chord Max Cl/Cd 169.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e397-il) EPPLER 397 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E397 human powered aircraft airfoil Max thickness 13.5% at 29.4% chord Max camber 5.3% at 52.1% chord Max Cl/Cd 169.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hs1708-il) HAM-STD HS1-708 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 7.9% at 22% chord Max camber 5% at 46% chord Max Cl/Cd 169 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(miley-il) MILEY M06-13-128		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Miley MO6-13-128 airfoil Max thickness 12.9% at 35% chord Max camber 4.9% at 35% chord Max Cl/Cd 168 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(nlf1015-il) NASA NLF1015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers-Maughmer NLF(1)-1015 natural laminar flow airfoil Max thickness 15% at 39.8% chord Max camber 4.3% at 62.8% chord Max Cl/Cd 167.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e377-il) EPPLER 377 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E377 ultralight airfoil Max thickness 3.9% at 8.4% chord Max camber 8.8% at 36.9% chord Max Cl/Cd 167.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(jn153-il) JN-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Narramore JN153 airfoil Max thickness 17.6% at 28.2% chord Max camber 8.4% at 38.1% chord Max Cl/Cd 165.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(dae11-il) DAE-11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE11 low Reynolds number airfoil Max thickness 12.8% at 32.8% chord Max camber 6.6% at 44.4% chord Max Cl/Cd 165 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e62-il) E62 (5.62%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E62 low Reynolds number airfoil Max thickness 5.6% at 26.2% chord Max camber 5% at 49.3% chord Max Cl/Cd 164.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database