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Airfoil database list (S).

S1010 HPV Airfoil to S2055

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(s1010-il) S1010 HPV airfoil

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S1010 HPV airfoilSelig S1010 HPV airfoil
Max thickness 6% at 23.3% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(s1012-il) S1012

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S1012Selig S1012 HPV airfoil
Max thickness 12% at 37.3% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(s1014-il) S1014

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S1014Selig 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

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S1016Selig 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.

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Ornithopter airfoil.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)

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SOMERS S102 AIRFOIL (BLUNT)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)

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SOMERS S102 AIRFOIL (SHARP)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)

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S1046 17% (Danny Howell)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)

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S1048 14% (Danny Howell)Selig S1048 airfoil
Max thickness 14% at 27% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(s1091-il) S1091

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S1091Selig 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%

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S1210 12%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

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S1221  w/ 4 deg flapSelig 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

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S1221  w/o flapSelig 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

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S1223Selig 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

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S1223 RTLRichard 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

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S2027Selig 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

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S2046Selig 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

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S2048Selig 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%

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S2050 8.93%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

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S2055Selig 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
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