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.

(sc20518-il) NASA SC(2)-0518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0518 airfoil (NASA TP-2969) Max thickness 18% at 35% chord Max camber 1.9% at 82% chord Max Cl/Cd 30.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e604-il) EPPLER 604 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E604 sailplane airfoil Max thickness 18.8% at 37.3% chord Max camber 3.4% at 42.3% chord Max Cl/Cd 30.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n64008a-il) NACA 64-008A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 30.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(k3-il) GRUMMAN K-3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman K-3 transonic airfoil (GAC .70-.83-17.5) Max thickness 17.3% at 33.1% chord Max camber 2.6% at 74.7% chord Max Cl/Cd 30.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 30.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(lwk80120k25-il) LWK 80-120/K25		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-120/K25 symmetrical airfoil Max thickness 12.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 30.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(cp-080-050-gn) Cambered plate C=8% T=5% R=1.6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=8% Wall thickness=5% Radius=1.603 Max thickness 8.4% at 5% chord Max camber 5.3% at 47% chord Max Cl/Cd 30.1 at Re# 100,000 Source Generated
(cp-080-050-gn) Cambered plate C=8% T=5% R=1.6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=8% Wall thickness=5% Radius=1.603 Max thickness 8.4% at 5% chord Max camber 5.3% at 47% chord Max Cl/Cd 30 at Re# 100,000 Source Generated
(n5h15-il) NACA 5-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-15 rotorcraft airfoil Max thickness 15.4% at 40% chord Max camber 2.9% at 30% chord Max Cl/Cd 30 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(b707b-il) BOEING 707 .19 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 12.1% at 29.9% chord Max camber 0.7% at 9.9% chord Max Cl/Cd 30 at Re# 100,000 Source UIUC Airfoil Coordinates Database