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.

(s9032-il) S9032 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 25% chord Max camber 0% at 0% chord Max Cl/Cd 43.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq07-il) HQ 0/7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/7 R/C sailplane airfoil Max thickness 7% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 43.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(b707a-il) BOEING 707 .08 SPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 707 airfoils Max thickness 11.4% at 24% chord Max camber 0.2% at 6% chord Max Cl/Cd 43.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20610-il) NASA SC(2)-0610 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0610 airfoil (NASA TP-2969) Max thickness 10% at 38% chord Max camber 1.8% at 82% chord Max Cl/Cd 43.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx73170-il) WORTMANN FX 73-170		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-170 airfoil Max thickness 17.1% at 43.5% chord Max camber 4.4% at 56.5% chord Max Cl/Cd 43.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(fx75vg166-il) FX 75-VG-166/22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 75-VG-166/22 variable geometry airfoil Max thickness 16.7% at 43.5% chord Max camber 2.4% at 40.2% chord Max Cl/Cd 43.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20412-il) NASA SC(2)-0412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0412 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.3% at 83% chord Max Cl/Cd 43 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(marske2-il) MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IA airfoil (NACA 23112/43012A hybrid) Max thickness 12.1% at 25% chord Max camber 2.7% at 15% chord Max Cl/Cd 43 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca0024-il) NACA 0024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0024 airfoil Max thickness 24% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 43 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s9033-il) S9033 (7.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane Max thickness 7.5% at 22.8% chord Max camber 0% at 0% chord Max Cl/Cd 42.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database