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.

(s3014-il) S3014-095-85		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3014 low Reynolds number airfoil Max thickness 9.5% at 29.4% chord Max camber 2.6% at 38.6% chord Max Cl/Cd 51.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe360-il) GOE 360 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 360 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.9% at 29.9% chord Max Cl/Cd 51.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq1585-il) HQ 1.5/8.5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/8.5 R/C sailplane airfoil Max thickness 8.6% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 51.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe493-il) GOE 493 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 493 airfoil Max thickness 14.9% at 29.3% chord Max camber 3.4% at 49.3% chord Max Cl/Cd 51.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(prandtl-d-root-ns) Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil Max thickness 12% at 30.9% chord Max camber 3.5% at 37.1% chord Max Cl/Cd 51.4 at Re# 100,000 Source NASA

(lrn1007-il) lrn1007		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LRN(1)-1007 low Reynolds number airfoil Max thickness 7.3% at 39.8% chord Max camber 5.9% at 44.6% chord Max Cl/Cd 51.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq159b-il) HQ 1.5/9 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/9 B R/C sailplane airfoil Max thickness 9% at 37.1% chord Max camber 1.5% at 50% chord Max Cl/Cd 51.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ste87391-il) EPPLER STE 87(-3)-914 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STE 87(-3)-914 airfoil Max thickness 14.6% at 34.1% chord Max camber 4.2% at 58.3% chord Max Cl/Cd 51.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq1510-il) HQ 1.5/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 51.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe612-il) GOE 612 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 612 airfoil Max thickness 15% at 29.5% chord Max camber 5% at 49.5% chord Max Cl/Cd 51.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database