Selig S1223 high lift low Reynolds number airfoilMax thickness 12.1% at 19.8% chord.Max camber 8.1% at 49% chordSource UIUC Airfoil Coordinates DatabaseSource dat fileThe dat file is in Selig format S1223 1.00000 0.00000 0.99838 0.00126 0.99417 0.00494 0.98825 0.01037 0.98075 0.01646 0.97111 ...
the rationality of the numerical simulation, the aerodynamic performance data of the numerical simulation are compared with the experimental data of airfoil S1223 with the relative thickness of 12.13%, which prove the numerical simulation of low-Reynolds-number and high-lift airfoil S1223 is ...
Details of airfoil (aerofoil)(s1223rtl-il) S1223 RTL Richard T. LaSalle modification of the S1223 to S1223RTL