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.

(npl9627-il) NPL 9627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9627 rotorcraft airfoil Max thickness 12.2% at 31% chord Max camber 0.9% at 40.4% chord Source UIUC Airfoil Coordinates Database
(e874-il) EPPLER 874 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E874 hydrofoil Max thickness 7.9% at 28.8% chord Max camber 0.9% at 35.7% chord Source UIUC Airfoil Coordinates Database
(supermarine371i-il) Supermarine 371-I (root)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-I root airfoil Max thickness 13% at 40% chord Max camber 0.9% at 50% chord Source UIUC Airfoil Coordinates Database
(ssca07-il) SIKORSKY SSC-A07 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Flemming SSC-A07 transonic rotorcraft airfoil Max thickness 7% at 37.7% chord Max camber 0.9% at 17.2% chord Source UIUC Airfoil Coordinates Database
(mh95-il) MH 95 15.86%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 95 parafoil Max thickness 15.8% at 33.6% chord Max camber 0.9% at 81.6% chord Source UIUC Airfoil Coordinates Database

(giiic-il) GIII BL75 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 9.9% at 39.8% chord Max camber 0.9% at 29.8% chord Source UIUC Airfoil Coordinates Database
(hq1012-il) HQ 1.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 1% at 50% chord Source UIUC Airfoil Coordinates Database
(hq1010-il) HQ 1.0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1% at 50% chord Source UIUC Airfoil Coordinates Database
(s809-nr) NREL's S809 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord Max camber 1% at 82.3% chord Source NWTC National WInd Technology Center
(raf25-il) RAF 25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-25 airfoil Max thickness 6.5% at 29.9% chord Max camber 1% at 49.9% chord Source UIUC Airfoil Coordinates Database