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.

(mh43-il) MH 43 8.5%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 43 for F3B and F3E Max thickness 8.5% at 31.4% chord Max camber 1.7% at 36.4% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe225-il) GOE 225 (MVA H.35) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 225 (MVA H.35) airfoil Max thickness 12.8% at 19.7% chord Max camber 7.6% at 49.7% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(l188tip-il) LOCKHEED L-188 TIP AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(pt40-il) PT40		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Plane PT-40 trainer airfoil Max thickness 11.6% at 27.1% chord Max camber 2.9% at 41.6% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe723-il) GOE 723 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 723 airfoil Max thickness 11.6% at 29.7% chord Max camber 4.5% at 49.7% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rhodesg32-il) Rhode St. Genese 32		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 32 airfoil Max thickness 11.9% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(giiih-il) GIII BL207 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 39.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(daytonwrightt1-il) Dayton-Wright T-1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dayton-Wright T-1 airfoil Max thickness 13.4% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe233-il) GOE 233 (MVA CA4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 233 (MVA CA4) airfoil Max thickness 11.6% at 19.8% chord Max camber 8.2% at 49.8% chord Max Cl/Cd 33.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database