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.

(pw51-pw) PW51		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Airfoil for plank model gliders Max thickness 8.9% at 27.5% chord Max camber 1.4% at 27.5% chord Max Cl/Cd 26.2 at Re# 50,000 Source RC Groups
(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord Max camber 1.3% at 20.1% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca23018-il) NACA 23018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23018 airfoil Max thickness 18% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(lwk80100-il) LWK 80-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-100 symmetrical airfoil Max thickness 10.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq07-il) HQ 0/7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/7 R/C sailplane airfoil Max thickness 7% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(e338-il) EPPLER 338 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E338 flying wing airfoil Max thickness 13.3% at 31.1% chord Max camber 3.7% at 26.2% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(bacnlf-il) BOEING HSNLF AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% chord Max Cl/Cd 26.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sd8020-il) SD8020-010-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD8020 low Reynolds number airfoil Max thickness 10.1% at 27.5% chord Max camber 0% at 42.1% chord Max Cl/Cd 26.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s4233-il) S4233-136-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4233 low Reynolds number airfoil Max thickness 13.6% at 34.9% chord Max camber 2.7% at 48.8% chord Max Cl/Cd 26.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe319-il) GOE 319 (HANSA-BRANDENBURG II) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 319 (Hansa-Brandenburg II) airfoil Max thickness 10.3% at 29.8% chord Max camber 5.8% at 29.8% chord Max Cl/Cd 26.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database