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Airfoil database list (S).

S1010 HPV Airfoil to S2055

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(s1010-il) S1010 HPV airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1010 HPV airfoil Max thickness 6% at 23.3% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s1012-il) S1012		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1012 HPV airfoil Max thickness 12% at 37.3% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s1014-il) S1014		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1014 HPV airfoil Max thickness 16.5% at 42.2% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s1016-il) S1016		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1016 HPV airfoil Max thickness 17.5% at 41.8% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s1020-il) Ornithopter airfoil.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1020 ornithopter airfoil Max thickness 15.1% at 33.8% chord Max camber 4.6% at 57% chord Source UIUC Airfoil Coordinates Database

(s102b-il) SOMERS S102 AIRFOIL (BLUNT)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2% at 68.7% chord Source UIUC Airfoil Coordinates Database
(s102s-il) SOMERS S102 AIRFOIL (SHARP)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2.1% at 68.7% chord Source UIUC Airfoil Coordinates Database
(s1046-il) S1046 17% (Danny Howell)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1046 airfoil Max thickness 17% at 30.8% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s1048-il) S1048 14% (Danny Howell)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1048 airfoil Max thickness 14% at 27% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s1091-il) S1091		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1091 airfoil Max thickness 5.1% at 13.4% chord Max camber 5.7% at 45.1% chord Source UIUC Airfoil Coordinates Database
(s1210-il) S1210 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1210 high lift low Reynolds number airfoil Max thickness 12% at 21.4% chord Max camber 6.7% at 51.1% chord Source UIUC Airfoil Coordinates Database
(s1221-flap-il) S1221 w/ 4 deg flap		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord Max camber 5.3% at 52.9% chord Source UIUC Airfoil Coordinates Database
(s1221-il) S1221 w/o flap		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1221 airfoil Max thickness 12.1% at 21.8% chord Max camber 4.9% at 49.1% chord Source UIUC Airfoil Coordinates Database

(s1223-il) S1223		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1223 high lift low Reynolds number airfoil Max thickness 12.1% at 19.8% chord Max camber 8.1% at 49% chord Source UIUC Airfoil Coordinates Database
(s1223rtl-il) S1223 RTL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Richard T. LaSalle modification of the S1223 to S1223RTL Max thickness 13.5% at 19.9% chord Max camber 8.3% at 55.2% chord Source UIUC Airfoil Coordinates Database
(s2027-il) S2027		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2027 low Reynolds number airfoil Max thickness 14.5% at 29.4% chord Max camber 2.7% at 38.3% chord Source UIUC Airfoil Coordinates Database
(s2046-il) S2046		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2046 low Reynolds number airfoil Max thickness 9% at 26.2% chord Max camber 2.6% at 55.1% chord Source UIUC Airfoil Coordinates Database
(s2048-il) S2048		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2048 low Reynolds number airfoil Max thickness 8.6% at 35.4% chord Max camber 1.7% at 60.1% chord Source UIUC Airfoil Coordinates Database
(s2050-il) S2050 8.93%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2050 low Reynolds number airfoil Max thickness 8.9% at 29.8% chord Max camber 1.1% at 69.5% chord Source UIUC Airfoil Coordinates Database
(s2055-il) S2055		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord Source UIUC Airfoil Coordinates Database