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.

(pmc19sm-il) PMC19 Smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	PMC19 Max thickness 9.2% at 34.2% chord Max camber 2.1% at 17.5% chord Max Cl/Cd 74 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf69-il) RAF 69 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-69 airfoil Max thickness 20.6% at 30% chord Max camber 1.7% at 50% chord Max Cl/Cd 74 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq1511-il) HQ 1.5/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 1.5% at 50% chord Max Cl/Cd 74 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rg14-il) RG 14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14 airfoil Max thickness 8.5% at 29.7% chord Max camber 1.6% at 39.2% chord Max Cl/Cd 74 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ncambre-il) ONERA NACA CAMBRE AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil Max thickness 11.5% at 31.2% chord Max camber 1.4% at 15.9% chord Max Cl/Cd 73.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(k1-il) NYU/GRUMMAN K-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NYU/Grumman K-1 transonic airfoil (GAC .75-.63-11.6) Max thickness 11.6% at 33% chord Max camber 1.9% at 75% chord Max Cl/Cd 73.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e361-il) EPPLER 361 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E361 rotorcraft airfoil Max thickness 12.1% at 37.1% chord Max camber 1.7% at 27.4% chord Max Cl/Cd 73.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe681-il) GOE 681 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 681 airfoil Max thickness 16.8% at 29.2% chord Max camber 4.4% at 39.2% chord Max Cl/Cd 73.9 at Re# 500,000 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 73.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(giiij-il) GIII BL332 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 8.5% at 35% chord Max camber 1.4% at 25% chord Max Cl/Cd 73.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database