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.

(sc1095-il) SIKORSKY SC1095 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Balch SC1095 rotorcraft airfoil Max thickness 9.5% at 26.9% chord Max camber 0.8% at 26.9% chord Max Cl/Cd 26.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n0012-il) NACA 0012 AIRFOILS		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 26.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(oa213-il) ONERA OA213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12.6% at 32.5% chord Max camber 3.3% at 25% chord Max Cl/Cd 26.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(pw98mod-pw) PW98-mod		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.4% at 27.5% chord Max camber 1.8% at 27.5% chord Max Cl/Cd 26.5 at Re# 50,000 Source RC Groups
(goe681-il) GOE 681 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 681 airfoil Max thickness 16.8% at 29.2% chord Max camber 4.4% at 39.2% chord Max Cl/Cd 26.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(sc2110-il) SIKORSKY SC2110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Lednicer & Owen SC2110 rotorcraft airfoil (SC5410) Max thickness 9.9% at 37.7% chord Max camber 1.9% at 15.7% chord Max Cl/Cd 26.5 at Re# 50,000 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 26.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e325-il) EPPLER 325 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E325 flying wing airfoil Max thickness 12.6% at 34.3% chord Max camber 1.8% at 16.3% chord Max Cl/Cd 26.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca001034a08cli02-il) NACA 0010-34 a=0.8 c(li)=0.2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-34 a=0.8 c(li)=0.2 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Max Cl/Cd 26.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(eh2510-il) EH 2.5/10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.5/10 for tailless R/C aircraft Max thickness 10% at 30% chord Max camber 2.5% at 25% chord Max Cl/Cd 26.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database