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Airfoil database list (U).

UA(2)-180 (University Of Alberta/Marsden) to USA 34 AIRFOIL

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(ua2-180-il) UA(2)-180 (University of Alberta/Marsden)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	UA(2)-180 airfoil for ultralight category aircraft Max thickness 18.1% at 31.5% chord Max camber 7% at 36.6% chord Source UIUC Airfoil Coordinates Database
(ua2-180sm-il) UA(2)-180 smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	UA(2)-180 (smoothed) airfoil for ultralight category aircraft Max thickness 18.2% at 34.1% chord Max camber 6.5% at 39.3% chord Source UIUC Airfoil Coordinates Database
(ua79sf18-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 FLAPPED sailplane airfoil Max thickness 18.8% at 42.8% chord Max camber 3.7% at 63.4% chord Source UIUC Airfoil Coordinates Database
(ua79sff-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 sailplane airfoil FLAP Max thickness 8.7% at 73.1% chord Max camber 3.4% at 78.1% chord Source UIUC Airfoil Coordinates Database
(ua79sfm-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 sailplane airfoil MAIN ELEMENT Max thickness 18.8% at 42.8% chord Max camber 3% at 66.9% chord Source UIUC Airfoil Coordinates Database

(uag8814320-il) UAG 88-143/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	UAG 88-143/20 airfoil Max thickness 14.3% at 43.5% chord Max camber 6.2% at 46.7% chord Source UIUC Airfoil Coordinates Database
(ui1720-il) UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Illinois UI-1720 high lift airfoil Max thickness 13.8% at 19% chord Max camber 4.6% at 21.2% chord Source UIUC Airfoil Coordinates Database
(ultimate-il) ULTIMATE		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Carl Goldberg R/C Ultimate Bipe airfoil Max thickness 12.8% at 34.2% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(us1000root-il) US1000ROOT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Planes R/C Ultra-Sport 1000 airfoil Max thickness 18.6% at 27.1% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(usa22-il) USA 22 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-22 airfoil Max thickness 9.1% at 19.9% chord Max camber 4.4% at 39.9% chord Source UIUC Airfoil Coordinates Database
(usa25-il) USA 25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-25 airfoil Max thickness 8.3% at 19.9% chord Max camber 5.2% at 29.9% chord Source UIUC Airfoil Coordinates Database
(usa26-il) USA 26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-26 airfoil Max thickness 9.8% at 19.9% chord Max camber 4.3% at 39.9% chord Source UIUC Airfoil Coordinates Database
(usa27-il) USA 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-27 airfoil Max thickness 11.1% at 30% chord Max camber 5.1% at 40% chord Source UIUC Airfoil Coordinates Database

(usa27m2-il) USA 27 mod. AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-27MOD airfoil Max thickness 13.3% at 30% chord Max camber 5% at 40% chord Source UIUC Airfoil Coordinates Database
(usa28-il) USA 28 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-28 airfoil Max thickness 13.2% at 29.9% chord Max camber 3.8% at 49.9% chord Source UIUC Airfoil Coordinates Database
(usa29-il) USA 29 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-29 airfoil Max thickness 13.2% at 29.7% chord Max camber 5.5% at 39.7% chord Source UIUC Airfoil Coordinates Database
(usa31-il) USA 31 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-31 airfoil Max thickness 14.8% at 19.7% chord Max camber 9.3% at 39.7% chord Source UIUC Airfoil Coordinates Database
(usa32-il) USA 32 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-32 airfoil Max thickness 14.7% at 19.8% chord Max camber 9.3% at 39.8% chord Source UIUC Airfoil Coordinates Database
(usa33-il) USA 33 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-33 airfoil Max thickness 14.2% at 29.9% chord Max camber 4.9% at 29.9% chord Source UIUC Airfoil Coordinates Database
(usa34-il) USA 34 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-34 airfoil Max thickness 18% at 29.5% chord Max camber 7.7% at 39.5% chord Source UIUC Airfoil Coordinates Database