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Airfoil database list (A).

AH 93-K-132/15 to ARA-D 13% AIRFOIL

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(ah93k132-il) AH 93-K-132/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-132/15 airfoil for use with flaps (K) Max thickness 13.2% at 41.2% chord Max camber 3.5% at 41.2% chord Source UIUC Airfoil Coordinates Database
(ah93w145-il) AH 93-W-145		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-145 airfoil for use on wind turbines (W) Max thickness 14.5% at 33.9% chord Max camber 3.9% at 37.1% chord Source UIUC Airfoil Coordinates Database
(ah93w174-il) AH 93-W-174		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-174 airfoil for use on wind turbines (W) Max thickness 17.4% at 33.9% chord Max camber 3.9% at 37.1% chord Source UIUC Airfoil Coordinates Database
(ah93w215-il) AH 93-W-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-215 airfoil for use on wind turbines (W) Max thickness 21.2% at 33.9% chord Max camber 3.1% at 40.2% chord Source UIUC Airfoil Coordinates Database
(ah93w257-il) AH 93-W-257		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-257 airfoil for use on wind turbines (W) Max thickness 25.7% at 30.9% chord Max camber 2.1% at 77.8% chord Source UIUC Airfoil Coordinates Database

(ah93w300-il) AH 93-W-300		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-300 airfoil for use on wind turbines (W) Max thickness 30% at 27.9% chord Max camber 1.6% at 72.1% 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
(ah94145-il) AH 94-145		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-145 airfoil Max thickness 14.6% at 38.9% chord Max camber 5.6% at 44.6% chord Source UIUC Airfoil Coordinates Database
(ah94156-il) AH 94-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-156 airfoil Max thickness 15.6% at 39.6% chord Max camber 3.6% at 41.5% chord Source UIUC Airfoil Coordinates Database
(ah94w301-il) AH 94-W-301		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-W-301 airfoil for use on wind turbines (W) Max thickness 30.1% at 30.9% chord Max camber 1.3% at 80.4% chord Source UIUC Airfoil Coordinates Database
(ah95160-il) AH 95-160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 95-160 airfoil Max thickness 16% at 38.9% chord Max camber 5.6% at 44.6% chord Source UIUC Airfoil Coordinates Database
(ames01-il) NASA/AMES A-01 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Hicks A-01 transonic rotorcraft airfoil Max thickness 10.3% at 35% chord Max camber 1.4% at 15% chord Source UIUC Airfoil Coordinates Database
(ames02-il) NASA/AMES A-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Hicks A-02 transonic rotorcraft airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord Source UIUC Airfoil Coordinates Database

(ames03-il) NASA/AMES A-03 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Kennelly A-03 transonic rotorcraft airfoil Max thickness 10% at 37.5% chord Max camber 1.2% at 17.5% chord Source UIUC Airfoil Coordinates Database
(amsoil1-il) RUTAN CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord Max camber 2.1% at 42% chord Source UIUC Airfoil Coordinates Database
(amsoil2-il) RUTAN WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer wing airfoil Max thickness 11.8% at 39% chord Max camber 1% at 48% chord Source UIUC Airfoil Coordinates Database
(apex16-il) Apex 16 (normalized using XFOIL date021206)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela Apex 16 low Reynolds number transonic research airfoil Max thickness 12.9% at 38.6% chord Max camber 2.4% at 59.6% chord Source UIUC Airfoil Coordinates Database
(aquilasm-il) AQUILA 9.3% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AQUILA R/C sailplane airfoil Max thickness 9.4% at 31.3% chord Max camber 4% at 34.7% chord Source UIUC Airfoil Coordinates Database
(arad10-il) ARA-D 10% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 10% thick propeller airfoil Max thickness 10% at 25% chord Max camber 4% at 35% chord Source UIUC Airfoil Coordinates Database
(arad13-il) ARA-D 13% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 13% thick propeller airfoil Max thickness 13% at 25% chord Max camber 3.6% at 30% chord Source UIUC Airfoil Coordinates Database