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.

(b737d-il) BOEING 737 OUTBOARD 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 737 airfoils Max thickness 10.8% at 40% chord Max camber 1.6% at 20% chord Source UIUC Airfoil Coordinates Database
(bacj-il) BOEING AIRFOIL J (no closed TE)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company airfoil J Max thickness 10.1% at 40% chord Max camber 1.7% at 78% chord Source UIUC Airfoil Coordinates Database
(bacnlf-il) BOEING HSNLF AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% chord Source UIUC Airfoil Coordinates Database
(bacxxx-il) BOEING BACXXX 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 BACXXX Energy Efficient Transport Program airfoil Max thickness 11.3% at 35% chord Max camber 1.4% at 15% chord Source UIUC Airfoil Coordinates Database
(bambino6-il) Bambino 6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bambino 6 airfoil Max thickness 12% at 40% chord Max camber 2.8% at 40% chord Source UIUC Airfoil Coordinates Database

(be50-il) BE50 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 25% chord Max camber 4.1% at 45% chord Source UIUC Airfoil Coordinates Database
(be50sm-il) BE50 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 23.8% chord Max camber 4% at 45.4% chord Source UIUC Airfoil Coordinates Database
(boe103-il) BOEING 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing 103 airfoil Max thickness 12.7% at 30% chord Max camber 3.6% at 40% chord Source UIUC Airfoil Coordinates Database
(boe106-il) BOEING 106 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing 106 airfoil Max thickness 13.1% at 30% chord Max camber 3.3% at 40% chord Source UIUC Airfoil Coordinates Database
(bqm34-il) RYAN BQM-34 FIREBEE WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Ryan BQM-34 Firebee wing airfoil (NACA 63-014A W/NACA 0014 nose and thinned to .09899 to account for sweep) Max thickness 9.9% at 32.5% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database