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.

(s8052-il) S8052 (11.88%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8052 low Reynolds number airfoil Max thickness 11.9% at 33.3% chord Max camber 1.2% at 44.2% chord Max Cl/Cd 32.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(l188root-il) LOCKHEED L-188 ROOT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 root airfoil NACA 0014 -1.10 40/1.051 Cli=.3 a=.8 Max thickness 14% at 41.3% chord Max camber 2% at 51.7% chord Max Cl/Cd 32.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa51-il) USA 51 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-51 airfoil Max thickness 9.3% at 30% chord Max camber 2.6% at 30% chord Max Cl/Cd 32.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag09-il) AG09		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG09 airfoil Max thickness 4.9% at 17.4% chord Max camber 1.8% at 34.1% chord Max Cl/Cd 32.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag35-il) AG35		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG35 airfoil Max thickness 8.7% at 27.9% chord Max camber 2.3% at 37% chord Max Cl/Cd 32.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(giiij-il) GIII BL332 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35% chord Max camber 1.4% at 25% chord Max Cl/Cd 32.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh200-il) MH 200 12.97%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 200 for a canard airplane (main wing) Max thickness 13% at 39.5% chord Max camber 2.1% at 49.8% chord Max Cl/Cd 32.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e557-il) EPPLER 557 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E557 general aviation airfoil Max thickness 16% at 30.2% chord Max camber 3.7% at 60.8% chord Max Cl/Cd 32.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq1512-il) HQ 1.5/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 32.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(giiie-il) GIII BL126 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.8% at 44.9% chord Max camber 1.2% at 29.9% chord Max Cl/Cd 32.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database