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.

(vr1-il) BOEING-VERTOL VR-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-1 rotorcraft airfoil Max thickness 11% at 35.3% chord Max camber 1.5% at 43.3% chord Max Cl/Cd 61.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(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 61 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rae100-il) RAE 100 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord Max Cl/Cd 60.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(b707b-il) BOEING 707 .19 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 12.1% at 29.9% chord Max camber 0.7% at 9.9% chord Max Cl/Cd 60.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s9026-il) S9026 (9.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9026 (9.5%) symmetrical horizontal stab airfoil used on the Opus R/C sailplane Max thickness 9.5% at 27.3% chord Max camber 0% at 0% chord Max Cl/Cd 60.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(mh95-il) MH 95 15.86%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 95 parafoil Max thickness 15.8% at 33.6% chord Max camber 0.9% at 81.6% chord Max Cl/Cd 60.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx38153-il) FX 38-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 38-153 airfoil Max thickness 15.5% at 43.5% chord Max camber 2.1% at 80.4% chord Max Cl/Cd 60.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n13-il) N-13		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-13 airfoil Max thickness 11.8% at 30% chord Max camber 0.1% at 95% chord Max Cl/Cd 60.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca64209-il) NACA 64-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 60.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(giiic-il) GIII BL75 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 9.9% at 39.8% chord Max camber 0.9% at 29.8% chord Max Cl/Cd 60.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database