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.

(s2060-il) S2060 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2060 low Reynolds number airfoil Max thickness 8% at 30.2% chord Max camber 1.6% at 49.7% chord Max Cl/Cd 70.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca652415-il) NACA 65(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(2)-415 airfoil Max thickness 15% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 70.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx05h126-il) WORTMANN FX 05-H-126 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 05-H-126 rotorcraft airfoil Max thickness 12.6% at 37.1% chord Max camber 4.4% at 37.1% chord Max Cl/Cd 70.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx61147-il) FX 61-147 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-147 airfoil Max thickness 14.8% at 33.9% chord Max camber 3.2% at 33.9% chord Max Cl/Cd 70.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s3002-il) SELIG 3002-099-83		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3002 low Reynolds number airfoil Max thickness 9.9% at 30.6% chord Max camber 2.3% at 49.8% chord Max Cl/Cd 70.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(lrn1015-il) NASA LRN 1015 (NASA TM 102840)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LRN 1015 airfoil used on the Northrop Grumman RQ-4 Global Hawk airfoil Max thickness 15.2% at 40% chord Max camber 4.9% at 44% chord Max Cl/Cd 70.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sd7037-il) SD7037-092-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7037 low Reynolds number airfoil Max thickness 9.2% at 26.1% chord Max camber 2.5% at 44.7% chord Max Cl/Cd 70.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(kc135b-il) KC-135 BL124.32 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 13% at 40% chord Max camber 1.4% at 20% chord Max Cl/Cd 70.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e552-il) EPPLER 552 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E552 general aviation airfoil Max thickness 18.4% at 32.4% chord Max camber 2.6% at 51.8% chord Max Cl/Cd 70.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n22-il) N-22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-22 airfoil Max thickness 12.4% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 70.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database