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.

(hq2510-il) HQ 2.5/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 2.5% at 50% chord Max Cl/Cd 72.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fxs21158-il) FX S 02/1-158 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX S 02/1-158 airfoil Max thickness 15.8% at 30.9% chord Max camber 3.5% at 37.1% chord Max Cl/Cd 72.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e207-il) E207 (12.04%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E207 low Reynolds number airfoil Max thickness 12% at 29.6% chord Max camber 2.5% at 38.6% chord Max Cl/Cd 72.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah93156-il) AH 93-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-156 airfoil Max thickness 15.7% at 39.5% chord Max camber 3.7% at 41.5% chord Max Cl/Cd 72.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe278-il) GOE 278 (DAIMLER IX) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 278 (DAIMLER IX) airfoil Max thickness 7.4% at 29.9% chord Max camber 4.3% at 29.9% chord Max Cl/Cd 72.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(boe106-il) BOEING 106 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing 106 airfoil Max thickness 13.1% at 30% chord Max camber 3.3% at 40% chord Max Cl/Cd 72.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(davis-il) Davis AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord Max camber 3.7% at 40% chord Max Cl/Cd 72.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(raf31-il) RAF 31 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-31 airfoil Max thickness 12.7% at 30% chord Max camber 2.1% at 50% chord Max Cl/Cd 72.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa28-il) USA 28 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-28 airfoil Max thickness 13.2% at 29.9% chord Max camber 3.8% at 49.9% chord Max Cl/Cd 72.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe316-il) GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 316 (Hansa-Brandenburg IV.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.2% at 29.9% chord Max Cl/Cd 72 at Re# 200,000 Source UIUC Airfoil Coordinates Database