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Airfoil database list (C).

LOCKHEED C-141 BL0 AIRFOIL to CLARK Y AIRFOIL

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(c141a-il) LOCKHEED C-141 BL0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 13% at 40.2% chord Max camber 1.1% at 64.5% chord Source UIUC Airfoil Coordinates Database
(c141b-il) LOCKHEED C-141 BL113.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 12.6% at 40.2% chord Max camber 1.1% at 64.5% chord Source UIUC Airfoil Coordinates Database
(c141c-il) LOCKHEED C-141 BL426.57 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 11% at 40.2% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(c141d-il) LOCKHEED C-141 BL610.61 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.8% at 40.2% chord Max camber 1.5% at 50% chord Source UIUC Airfoil Coordinates Database
(c141e-il) LOCKHEED C-141 BL761.11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.5% at 40.2% chord Max camber 1.8% at 50% chord Source UIUC Airfoil Coordinates Database

(c141f-il) LOCKHEED C-141 BL958.89 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10% at 40.2% chord Max camber 2.3% at 45.1% chord Source UIUC Airfoil Coordinates Database
(c5a-il) LOCKHEED C-5A BL0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 13.1% at 40% chord Max camber 0.7% at 85% chord Source UIUC Airfoil Coordinates Database
(c5b-il) LOCKHEED C-5A BL488.2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.5% at 40% chord Max camber 1.2% at 70% chord Source UIUC Airfoil Coordinates Database
(c5c-il) LOCKHEED C-5A BL576 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 65% chord Source UIUC Airfoil Coordinates Database
(c5d-il) LOCKHEED C-5A BL758.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 60% chord Source UIUC Airfoil Coordinates Database
(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord Max camber 1.4% at 30% chord Source UIUC Airfoil Coordinates Database
(cap21c-il) CAP 21 (TraCFoil)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord Source UIUC Airfoil Coordinates Database
(cast102-il) CAST 10-2/DOA 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord Source UIUC Airfoil Coordinates Database

(ch10sm-il) CH10 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil Max thickness 12.8% at 30.6% chord Max camber 10.2% at 49.3% chord Source UIUC Airfoil Coordinates Database
(chen-il) CHEN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Illinois at Urbana-Champaign / Chen high lift airfoil Max thickness 12.5% at 27.7% chord Max camber 7.8% at 25.4% chord Source UIUC Airfoil Coordinates Database
(clarkk-il) CLARK K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord Source UIUC Airfoil Coordinates Database
(clarkv-il) CLARK V AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord Source UIUC Airfoil Coordinates Database
(clarkw-il) CLARK W AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK W airfoil Max thickness 11.2% at 30% chord Max camber 3.7% at 40% chord Source UIUC Airfoil Coordinates Database
(clarkx-il) CLARK X AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK X airfoil Max thickness 11.7% at 30% chord Max camber 3.3% at 40% chord Source UIUC Airfoil Coordinates Database
(clarky-il) CLARK Y AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK Y airfoil Max thickness 11.7% at 28% chord Max camber 3.4% at 42% chord Source UIUC Airfoil Coordinates Database