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.

(goe598-il) GOE 598 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 598 airfoil Max thickness 6.5% at 39.8% chord Max camber 1% at 49.8% chord Max Cl/Cd 54.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hor04-il) ONERA HOR04 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 4.1% at 33.2% chord Max camber 1.4% at 38.3% chord Max Cl/Cd 54.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(p51dtip-il) P-51D TIP (BL215) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord Max Cl/Cd 54.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(glennmartin3-il) Glenn Martin 3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 3 airfoil Max thickness 13.8% at 30% chord Max camber 4.6% at 30% chord Max Cl/Cd 54.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s815-nr) NREL's S815 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef Max thickness 26.2% at 25.7% chord Max camber 2.9% at 77.9% chord Max Cl/Cd 54.8 at Re# 200,000 Source NWTC National WInd Technology Center

(goe572-il) GOE 572 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 572 airfoil Max thickness 18.6% at 29.9% chord Max camber 8.3% at 29.9% chord Max Cl/Cd 54.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rc510-il) NASA RC(5)-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC(5)-10 rotorcraft airfoil Max thickness 10% at 40.1% chord Max camber 2.2% at 25.3% chord Max Cl/Cd 54.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh27-il) MH 27 11.99%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 27 for F3D Pylon Racing (extended laminar flow) Max thickness 12% at 42.4% chord Max camber 1.4% at 42.4% chord Max Cl/Cd 54.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh92-il) MH 92 15.49%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 92 parafoil Max thickness 15.5% at 27.4% chord Max camber 1.4% at 15.1% chord Max Cl/Cd 54.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s832-nr) NREL's S832 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S832 Max thickness 14.9% at 44% chord Max camber 5.3% at 44% chord Max Cl/Cd 54.7 at Re# 200,000 Source NWTC National WInd Technology Center