Reivindicaciones
1. A computer-aided method suitable for assisting in the design of an aircraft by providing dimensioning aerodynamic forces, skin values or values distributions around an airfoil corresponding to an aircraft component in transonic conditions inside a predefined parameter space by means of a reconstruction of the CFD computations for an initial group of points in the parameter space using a reduced-order model, generated by computing the POD modes of the flow variables and obtaining the POD coefficients using a genetic algorithm (GA) that minimizes the error associated to the reduced-order model, characterized in that it comprises the following steps: a) Decomposing for each flow variable the complete flow field (CFF) into a smooth field (SF) and a shock wave field (SWF) in each of said computations for an initial group of points; b) Obtaining the POD modes associated with the smooth field (SF) and the shock wave field (SWF) considering all said computations; c) 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; d) Calculating said aerodynamic forces, skin values or values distribution for whatever combination of values of said parameters using the reduced-order model obtained in previous steps. 2. A computer-aided method according to claim 1, characterized in that said step a) comprises the following sub-steps: a1) Obtaining the position and the trace of the shock wave for each of said computations; a2) Obtaining the smooth field (SF) and the shock wave field (SFW) for each of said computations; a3) Obtaining the internal shape and jump of the shock wave for each of said computations and for each of said flow variables; 3. A computer-aided method according to any of claims 1-2, characterized in that said step b) comprises the following sub-steps: b1) Obtaining the POD manifold for the internal shape of the shock wave; b2) Dividing the smooth field (SF) into two regions in the pressure and suction sides; b3) Selecting a set of convenient computations to calculate the POD modes of the smooth field (SF); b4) Obtaining the POD manifold for the smooth field (SF) and the complete flow field (CFF); b5) Obtaining an initial guess of the POD mode amplitudes. 4. A computer-aided method according to any of claims 1-3, characterized in that said step c) is performed iterating the following sub-steps: c1) GA minimization of a residual to calculate the POD mode amplitudes of the smooth field (SF); c2) GA minimization of a residual to obtain the position, the trace, and the internal structure of the shock wave. 5. A computer-aided method according to any of claims 1-4, characterized in that said predefined parameter space includes one or more of the following parameters: angle of attack, Mach number, sideslip angle, wing aileron deflection angle, spoilers deflection, high lift devices deflection, canard deflection, landing gear deflected status, landing gear doors angle, APU inlet open angle, the vertical tailplane rudder deflection angle, the horizontal tailplane elevator angle, the horizontal tailplane setting angle. 6. A computer-aided method according to any of claims 1-5, characterized in that said values distribution is one or a combination of the following: the pressure distribution, the velocity components distribution, the mach number (euler computation) distribution, the friction components distribution, the temperature distribution, the density distribution, the energy distribution, the entropy distribution, the enthalpy distribution. 7. A computer-aided method according to any of claims 1-6, characterized in that said aerodynamic forces include one or more of the following: the lift force, the drag force, the lateral force, the pitching moment, the rolling moment and the yawing moment of the aircraft component being designed. 8. A computer-aided method according to any of claims 1-7, characterized in that said aircraft component is one of the following: a wing, an horizontal tailplane, a vertical tailplane, fuselage, a high lift device, a spoiler, an engine, a canard. 9. 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, caracterized 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.
