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.

(mh61-il) MH 61 10.26%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 61 for flying wings Max thickness 10.2% at 27.6% chord Max camber 1.4% at 37.3% chord Max Cl/Cd 33 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rg12-il) RG-12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12 airfoil Max thickness 9.3% at 34.4% chord Max camber 1.4% at 34.4% chord Max Cl/Cd 32.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe401-il) GOE 401 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 401 airfoil Max thickness 7.1% at 29.9% chord Max camber 4.9% at 29.9% chord Max Cl/Cd 32.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca64a210-il) NACA 64A210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A210 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Max Cl/Cd 32.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca63209-il) NACA 63-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord Max Cl/Cd 32.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ag09-il) AG09		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG09 airfoil Max thickness 4.9% at 17.4% chord Max camber 1.8% at 34.1% chord Max Cl/Cd 32.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq1010-il) HQ 1.0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 32.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(giiie-il) GIII BL126 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 8.8% at 44.9% chord Max camber 1.2% at 29.9% chord Max Cl/Cd 32.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh25-il) MH 25 9.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 25 for F3D Pylon Racing (extended laminar flow) Max thickness 10% at 42.2% chord Max camber 1.4% at 42.2% chord Max Cl/Cd 32.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah79100b-il) AH 79-100 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-100B airfoil Max thickness 10% at 30.9% chord Max camber 6.4% at 50% chord Max Cl/Cd 32.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database