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.

(mrc-16-il) MRC-16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela MRC-16 Max thickness 13.9% at 34.6% chord Max camber 3% at 40.3% chord Max Cl/Cd 23.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx74130wp2-il) 74-130 WP2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann 74-130 WP2 airfoil Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord Max Cl/Cd 23.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca4418-il) NACA 4418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4418 airfoil Max thickness 18% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 23.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(k3-il) GRUMMAN K-3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman K-3 transonic airfoil (GAC .70-.83-17.5) Max thickness 17.3% at 33.1% chord Max camber 2.6% at 74.7% chord Max Cl/Cd 23 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e230-il) E230 (9.96%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E230 airfoil Max thickness 10% at 29.3% chord Max camber 0% at 0% chord Max Cl/Cd 23 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(joukowsk0018-jf) Joukovsky f=0% t=18%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	Joukowski 18% symmetrical airfoil Max thickness 18% at 27.1% chord Max camber 0% at 0% chord Max Cl/Cd 23 at Re# 50,000 Source Javafoil generated
(goe265-il) GOE 265 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 265 airfoil Max thickness 7.7% at 14.9% chord Max camber 7.3% at 39.9% chord Max Cl/Cd 23 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e855-il) EPPLER 855 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E855 propeller airfoil Max thickness 15.7% at 32.2% chord Max camber 3.7% at 50.6% chord Max Cl/Cd 23 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx62k153-il) FX 62-K-153/20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 62-K-153/20 airfoil Max thickness 15.3% at 40.2% chord Max camber 4.1% at 62.9% chord Max Cl/Cd 23 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah63k127-il) AH 63-K-127/24		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 63-K-127/24 airfoil for use with flaps (K) Max thickness 12.7% at 40.2% chord Max camber 3.8% at 43.5% chord Max Cl/Cd 23 at Re# 50,000 Source UIUC Airfoil Coordinates Database