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.

(hq1512-il) HQ 1.5/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 93.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe434-il) GOE 434 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 434 airfoil Max thickness 22.8% at 28.4% chord Max camber 5.2% at 48.5% chord Max Cl/Cd 93.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(cast102-il) CAST 10-2/DOA 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord Max Cl/Cd 93.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe13k-il) GOE 13K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 13K airfoil Max thickness 14.8% at 50% chord Max camber 5.5% at 60% chord Max Cl/Cd 93.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ag14-il) AG14		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG14 airfoil Max thickness 5.4% at 19.9% chord Max camber 2% at 41.9% chord Max Cl/Cd 93.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(mh108-il) MH 108 11.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 108 for stall controlled wind turbines Max thickness 11.9% at 22.8% chord Max camber 1% at 22.8% chord Max Cl/Cd 93.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(pmc19sm-il) PMC19 Smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	PMC19 Max thickness 9.2% at 34.2% chord Max camber 2.1% at 17.5% chord Max Cl/Cd 93.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(oa213-il) ONERA OA213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12.6% at 32.5% chord Max camber 3.3% at 25% chord Max Cl/Cd 93.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sd7003-il) SD7003-085-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7003 low Reynolds number airfoil Max thickness 8.5% at 24.4% chord Max camber 1.2% at 38.3% chord Max Cl/Cd 93.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e340-il) EPPLER 340 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E340 flying wing airfoil Max thickness 13.7% at 28.8% chord Max camber 2.6% at 19.7% chord Max Cl/Cd 93.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database