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.

(goe134-il) GOE 134 (MVA H.12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 134 (MVA H.12) airfoil Max thickness 9.5% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(stcyr24-il) St. CYR 24 (Bartel 35-IIIC)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 24 (Bartel 35-IIIC) airfoil Max thickness 12.4% at 30% chord Max camber 5.9% at 40% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(vr11x-il) BOEING-VERTOL VR-11X AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/NASA/Dadone VR-11X transonic rotorcraft airfoil Max thickness 11% at 40% chord Max camber 2.4% at 25% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mrc-20-il) MRC-20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela MRC-20 Max thickness 15.6% at 38.2% chord Max camber 2.9% at 48% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e171-il) (Dicke 12.28%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E171 low Reynolds number airfoil Max thickness 12.3% at 32.4% chord Max camber 0% at 0% chord Max Cl/Cd 29.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(e297-il) EPPLER 297 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E297 tailplane airfoil Max thickness 11.4% at 37.7% chord Max camber 0% at 0% chord Max Cl/Cd 29.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca641112-il) NACA 64(1)-112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-112 airfoil Max thickness 12% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 29.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sd7003-il) SD7003-085-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7003 low Reynolds number airfoil Max thickness 8.5% at 24.4% chord Max camber 1.2% at 38.3% chord Max Cl/Cd 29.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s825-nr) NREL's S825 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S825 primary 17.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=1.44 Clmax(R)=1.37 High max lift coef Max thickness 17.1% at 29.9% chord Max camber 3.9% at 65.3% chord Max Cl/Cd 29.3 at Re# 50,000 Source NWTC National WInd Technology Center
(c141b-il) LOCKHEED C-141 BL113.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 12.6% at 40.2% chord Max camber 1.1% at 64.5% chord Max Cl/Cd 29.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database