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.

(hq3518-il) HQ 3.5/18 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/18 R/C sailplane airfoil Max thickness 18% at 35% chord Max camber 3.5% at 50% chord Source UIUC Airfoil Coordinates Database
(hq358-il) HQ 3.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 3.5% at 50% chord Source UIUC Airfoil Coordinates Database
(hq359-il) HQ 3.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3.5% at 50% chord Source UIUC Airfoil Coordinates Database
(n8h12-il) NACA 8-H-12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 8-H-12 rotorcraft airfoil Max thickness 12% at 30% chord Max camber 3.5% at 30% chord Source UIUC Airfoil Coordinates Database
(prandtl-d-root-ns) Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil Max thickness 12% at 30.9% chord Max camber 3.5% at 37.1% chord Source NASA

(sd7062-il) SD7062 (14%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7062 low Reynolds number airfoil Max thickness 14% at 25.5% chord Max camber 3.5% at 38.8% chord Source UIUC Airfoil Coordinates Database
(ah79100a-il) AH 79-100 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-100A airfoil Max thickness 10% at 27.9% chord Max camber 3.6% at 56.5% chord Source UIUC Airfoil Coordinates Database
(ah82150f-il) AH 82-150 F		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 82-150 F airfoil Max thickness 15% at 43.5% chord Max camber 3.6% at 46.7% chord Source UIUC Airfoil Coordinates Database
(ah93k131-il) AH 93-K-131/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-131/15 airfoil for use with flaps (K) Max thickness 13.1% at 41.3% chord Max camber 3.6% at 41.3% chord Source UIUC Airfoil Coordinates Database
(ah93w480b-il) AH 93-W-480B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-480B airfoil for use on wind turbines (W) Max thickness 47.8% at 44.1% chord Max camber 3.6% at 44.1% chord Source UIUC Airfoil Coordinates Database