Method and system for a quick calculation of aerodynamic forces on an aircraft in transonic conditions

A system for assisting in the design of an aircraft by providing the dimensioning aerodynamic forces, skin values or values distribution around an airfoil corresponding to an aircraft component in transonic conditions inside a predefined parameter space, comprising:

• a) A computer-implemented discrete model of said aircraft component and the surrounding flow field;
• b) A computer-implemented CFD module for calculating and storing said fluid dynamic forces, skin values or values distribution for an initial group of points in the parameter space;
• c) A computer-implemented POD reduced order model module for performing calculations of said aerodynamic forces, skin values or values distribution for any point in the parameter space, characterized in that,
• d) said computer-implemented CFD module comprises suitable means for decomposing for each flow variable the complete flow field (CFF) into a smooth field (SF) and a shock wave field (SWF)
• e) said computer-implemented POD reduced order-model comprises suitable means for obtaining the POD modes associated with the smooth field (SF) and shock wave field (SWF) considering a selected group of CFD computations and for obtaining the POD coefficients using a genetic algorithm (GA) that minimizes a fitness function defined using a residual calculated from the Euler equations and boundary conditions.