Prediction and Plotting of Aerodynamic Performance of Airfoils

Input flight conditions and CST parameters to rapidly generate airfoil geometry and predict Cl/Cd/Cm. Supports 5-fold cross-validation for integrated inference, with results including L/D for auxiliary evaluation.

Plotting Function (CST → Airfoil)

The first four parameters correspond to the lower airfoil surface wl, and the last four to the upper airfoil surface wu. The trailing edge thickness dz is optional.

Prediction Function (Re, alpha, CST → Cl / Cd / Cm)

Input 2 flight conditions + 8 CST parameters, and perform inference using the 5-fold integrated model.