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.

(sg6050-il) SG6050		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6050 wind turbine airfoil Max thickness 16% at 31.5% chord Max camber 3.1% at 48.9% chord Source UIUC Airfoil Coordinates Database
(sm701-il) SM701		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Somers / Maughmer SM701 airfoil Max thickness 16% at 36.3% chord Max camber 3% at 60.3% chord Source UIUC Airfoil Coordinates Database
(stcyr234-il) St. CYR 234 (Bartel 17-IC)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 234 (Bartel 17-IC) airfoil Max thickness 16% at 20% chord Max camber 5.1% at 50% chord Source UIUC Airfoil Coordinates Database
(ah83159-il) AH 83-159		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord Max camber 3.8% at 40.2% chord Source UIUC Airfoil Coordinates Database
(davis-corrected-il) DAVIS BASIC B-24 WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Davis basic B-24 wing airfoil Max thickness 15.9% at 29.6% chord Max camber 2.5% at 29.6% chord Source UIUC Airfoil Coordinates Database
(e1210-il) EPPLER 1210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord Source UIUC Airfoil Coordinates Database
(goe498-il) GOE 498 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 498 airfoil Max thickness 15.9% at 29.4% chord Max camber 5.5% at 49.4% chord Source UIUC Airfoil Coordinates Database
(goe502-il) GOE 502 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 502 airfoil Max thickness 15.9% at 29.3% chord Max camber 6.1% at 49.4% chord Source UIUC Airfoil Coordinates Database
(la5055-il) LIEBECK LA5055 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Liebeck high lift airfoil Max thickness 15.9% at 35% chord Max camber 5.9% at 40% chord Source UIUC Airfoil Coordinates Database
(nlf416-il) NASA/LANGLEY NLF(1)-0416 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil Max thickness 15.9% at 30.4% chord Max camber 2.5% at 34.8% chord Source UIUC Airfoil Coordinates Database

Page 32 of 164     22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41     Next

Please see the source web site or designer for any license conditions.