Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(goe165-il) GOE 165 (MVA MK.11) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 165 (MVA MK.11) airfoil Max thickness 12.1% at 19.7% chord Max camber 5.7% at 49.7% chord Max Cl/Cd 79.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq2195-il) HQ 2.1/9.5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.1/9.5 R/C sailplane airfoil Max thickness 9.5% at 35% chord Max camber 2.1% at 55% chord Max Cl/Cd 79 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx69h098-il) BELL/WORTMANN FX 69-H-098 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/Wortmann FX 69-H-098 rotorcraft airfoil Max thickness 9.9% at 28.2% chord Max camber 1.7% at 22.5% chord Max Cl/Cd 79 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(marske3-il) MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IID root airfoil (NACA 43012A/24112 hybrid) Max thickness 12.1% at 30% chord Max camber 2.8% at 15% chord Max Cl/Cd 79 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(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 79 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(rg15-il) RG-15 8.9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 15 low Reynolds number airfoil Max thickness 8.9% at 30.2% chord Max camber 1.8% at 39.7% chord Max Cl/Cd 79 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(giiif-il) GIII BL145 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 44.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 78.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq2010-il) HQ 2.0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 2% at 45% chord Max Cl/Cd 78.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rg14a147-il) RG 14A-1.4/7.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14A-1.4/7.0 airfoil Max thickness 7% at 29.7% chord Max camber 1.4% at 34.3% chord Max Cl/Cd 78.9 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 78.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database