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.

(naca0018-il) NACA 0018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 50.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s810-nr) NREL's S810 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S810 tip Max thickness 18% at 44.2% chord Max camber 0.9% at 10.9% chord Max Cl/Cd 50 at Re# 200,000 Source NWTC National WInd Technology Center
(fx78k150-il) FX 78-K-150/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 78-K-150/20 airfoil for use with flaps (K) Max thickness 15.1% at 43.5% chord Max camber 4.3% at 43.5% chord Max Cl/Cd 50 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx83w227-il) FX 83-W-227		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 83-W-227 airfoil for use on wind turbines (W) Max thickness 22.6% at 33.9% chord Max camber 3.4% at 40.2% chord Max Cl/Cd 50 at Re# 200,000 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 50 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe559-il) GOE 559 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 559 airfoil Max thickness 11.2% at 30% chord Max camber 3.4% at 30% chord Max Cl/Cd 50 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ssca09-il) SIKORSKY SSC-A09 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Flemming SSC-A09 transonic rotorcraft airfoil Max thickness 9% at 37.7% chord Max camber 1.2% at 17.2% chord Max Cl/Cd 50 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hsnlf213-il) HSNLF(1)-0213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley HSNLF(1)-0213 high speed natural laminar flow airfoil Max thickness 13.3% at 42.4% chord Max camber 1.4% at 32.4% chord Max Cl/Cd 49.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n64015a-il) NACA 642-015A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-015A airfoil Max thickness 15% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 49.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx66196v-il) FX 66-S-196 V1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-196 V1 airfoil Max thickness 19.6% at 37.1% chord Max camber 4% at 46.7% chord Max Cl/Cd 49.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database