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.

(ua79sf18-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 FLAPPED sailplane airfoil Max thickness 18.8% at 42.8% chord Max camber 3.7% at 63.4% chord Max Cl/Cd 37.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(a63a108c-il) NASA/AMES 63A108 MOD C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES modification of the NACA 63A-108 airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord Max Cl/Cd 37.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca0024-il) NACA 0024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0024 airfoil Max thickness 24% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 37 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(stcyr171-il) St. CYR 171 (Royer)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 171 (Royer) airfoil Max thickness 11.1% at 30% chord Max camber 1.5% at 50% chord Max Cl/Cd 36.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca64a010-il) NACA 64A-010 10.0%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A010 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 36.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(sc20406-il) NASA SC(2)-0406 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0406 airfoil (NASA TP-2969) Max thickness 6% at 35% chord Max camber 0.6% at 79% chord Max Cl/Cd 36.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m2-il) NACA M2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-2 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 36.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq07-il) HQ 0/7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/7 R/C sailplane airfoil Max thickness 7% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 36.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s831-nr) NREL's S831 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S831 tip 18.0% Dia=40 to 50 m Re=3.5E+6 Clmax(S)=1.50 Clmax(R)=1.48 High max lift coef Max thickness 18% at 44.2% chord Max camber 5% at 53.1% chord Max Cl/Cd 36.7 at Re# 200,000 Source NWTC National WInd Technology Center
(rae104-il) RAE 104 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 104 airfoil Max thickness 10% at 42% chord Max camber 0% at 0% chord Max Cl/Cd 36.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database