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.

(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 Max Cl/Cd 50.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(v43012-il) BOEING VERTOL V43012-1.58 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V43012-1.58 rotorcraft airfoil Max thickness 12% at 32% chord Max camber 3.7% at 15% chord Max Cl/Cd 50.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ms313-il) NASA/LANGLEY MS(1)-0313 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley MS(1)-0313 general aviation airfoil (buggy Max thickness 13.1% at 37.5% chord Max camber 1.8% at 67.5% chord Max Cl/Cd 50.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ht23-il) HT23		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT23 airfoil Max thickness 6.5% at 20.8% chord Max camber 1.1% at 22.6% chord Max Cl/Cd 50.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa32-il) USA 32 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-32 airfoil Max thickness 14.7% at 19.8% chord Max camber 9.3% at 39.8% chord Max Cl/Cd 50.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(c5b-il) LOCKHEED C-5A BL488.2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.5% at 40% chord Max camber 1.2% at 70% chord Max Cl/Cd 50.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh80-il) MH 80 12.72%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 80 for flying wings (hang glider) Max thickness 12.7% at 21.7% chord Max camber 2.8% at 21.7% chord Max Cl/Cd 50.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(marske4-il) MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.833 HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IID tip airfoil (NACA 43012A*.833 hybrid) Max thickness 10.2% at 20% chord Max camber 2.8% at 15% chord Max Cl/Cd 50.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca65209-il) NACA 65-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 50.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(stcyr172-il) St. CYR 172 (Royer)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 172 (Royer) airfoil Max thickness 13.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 50.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database