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.

(b707c-il) BOEING 707 .40 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 9.6% at 30% chord Max camber 1.9% at 15% chord Max Cl/Cd 34.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh91-il) MH 91 14.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 91 parafoil Max thickness 15% at 27.3% chord Max camber 1.4% at 18.7% chord Max Cl/Cd 34.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx66a175-il) WORTMANN FX 66-17A-175 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-17A-175 airfoil Max thickness 17.5% at 33.9% chord Max camber 4.2% at 40.2% chord Max Cl/Cd 34.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s9032-il) S9032 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 25% chord Max camber 0% at 0% chord Max Cl/Cd 34.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe504-il) GOE 504 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 504 airfoil Max thickness 18% at 29.2% chord Max camber 5.4% at 39.2% chord Max Cl/Cd 34.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(e339-il) EPPLER 339 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E339 flying wing airfoil Max thickness 13.5% at 30.1% chord Max camber 4.1% at 25.2% chord Max Cl/Cd 34.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s830-nr) NREL's S830 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S830 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.60 Clmax(R)=1.57 High max lift coef Max thickness 21% at 38.4% chord Max camber 4.4% at 70.5% chord Max Cl/Cd 34.2 at Re# 100,000 Source NWTC National WInd Technology Center
(fx711525-il) FX 71-L-150/25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-L-150/25 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 34.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(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 34.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq17-il) HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Airfoil measured from an ASW22 wing Max thickness 15.2% at 42% chord Max camber 4.5% at 42% chord Max Cl/Cd 34.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database