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.

(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 35.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e193-il) E193 (10.22%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E193 low Reynolds number airfoil Max thickness 10.2% at 31% chord Max camber 3% at 44.7% chord Max Cl/Cd 35.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(raf6-il) RAF 6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-6 airfoil Max thickness 10% at 30% chord Max camber 4.6% at 30% chord Max Cl/Cd 35.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(lrn1007-il) lrn1007		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LRN(1)-1007 low Reynolds number airfoil Max thickness 7.3% at 39.8% chord Max camber 5.9% at 44.6% chord Max Cl/Cd 35.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh30-il) MH 30 7.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 30 for F3E and F3B Max thickness 7.8% at 31% chord Max camber 1.7% at 46.4% chord Max Cl/Cd 35.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe574-il) GOE 574 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 574 airfoil Max thickness 10.3% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 35.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(b707e-il) BOEING 707 .99 SPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 707 airfoils Max thickness 9% at 42% chord Max camber 1.8% at 34% chord Max Cl/Cd 35.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq158-il) HQ 1.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/8 R/C sailplane airfoil Max thickness 8% at 32.5% chord Max camber 1.5% at 50% chord Max Cl/Cd 35.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s4061-il) S4061-096-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4061 low Reynolds number airfoil Max thickness 9.6% at 30.9% chord Max camber 3.3% at 44.7% chord Max Cl/Cd 35.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fxm2-il) WORTMANN FX M2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX M2 airfoil Max thickness 8.4% at 19.6% chord Max camber 4.8% at 30.9% chord Max Cl/Cd 35.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database