Computer implemented performance simulation procedure for a first rotor and/or a second rotor of a rotary wing aircraft to obtain real-time simulation for the training of pilots of rotary wing aircraft, which comprises the operations to: determine the geometric data of one blade of the first rotor, on the basis of which the movement of this first rotor is determined; determine the blade's local angle of attack α r, and the local Mach number M; determine the external actions that act on a blade in each iteration of a plurality of iterations and each blade's local lift, drag and moment coefficients c l, c d and c m, respectively, discretize the blades of the first rotor into blade elements to identify the dynamic balance of this first rotor, such that a) the discretization is done on the first rotor disc and, therefore, each of these blade elements is linked to this first rotor disc, which does not rotate, and b) this discretization divides the first rotor disc into n a sectors and each blade longitudinally into n e blade elements, characterized in that it also comprises the operation to: calculate, at the end of each iteration, the induced velocity for each blade element, which will be used in the next iteration to obtain the aerodynamic velocity of the blade element, and for simulating interference between the first rotor and a very close second rotor, e.g. a tandem rotor or a rotor counter-rotating on the same axis as the first rotor, the procedure also comprises: inclusion, in the calculation of the aerodynamic velocity of each blade element of each rotor, of not only its own induced velocity but also that of the other rotor, to obtain a reference induced velocity v i p, resulting from the action of this secondary rotor prevailing at a specific point of the first rotor disc, defined by its coordinates (r ip, ψ ip), and filtering of this reference induced velocity v i p. determine the geometric data of one blade of the first rotor, on the basis of which the movement of this first rotor is determined; determine the blade's local angle of attack α r, and the local Mach number M; determine the external actions that act on a blade in each iteration of a plurality of iterations and each blade's local lift, drag and moment coefficients c l, c d and c m, respectively, discretize the blades of the first rotor into blade elements to identify the dynamic balance of this first rotor, such that a) the discretization is done on the first rotor disc and, therefore, each of these blade elements is linked to this first rotor disc, which does not rotate, and b) this discretization divides the first rotor disc into n a sectors and each blade longitudinally into n e blade elements, a) the discretization is done on the first rotor disc and, therefore, each of these blade elements is linked to this first rotor disc, which does not rotate, and b) this discretization divides the first rotor disc into n a sectors and each blade longitudinally into n e blade elements, characterized in that it also comprises the operation to: calculate, at the end of each iteration, the induced velocity for each blade element, which will be used in the next iteration to obtain the aerodynamic velocity of the blade element, and for simulating interference between the first rotor and a very close second rotor, e.g. a tandem rotor or a rotor counter-rotating on the same axis as the first rotor, the procedure also comprises: inclusion, in the calculation of the aerodynamic velocity of each blade element of each rotor, of not only its own induced velocity but also that of the other rotor, to obtain a reference induced velocity v i p, resulting from the action of this secondary rotor prevailing at a specific point of the first rotor disc, defined by its coordinates (r ip, ψ ip), and filtering of this reference induced velocity v i p. calculate, at the end of each iteration, the induced velocity for each blade element, which will be used in the next iteration to obtain the aerodynamic velocity of the blade element, and for simulating interference between the first rotor and a very close second rotor, e.g. a tandem rotor or a rotor counter-rotating on the same axis as the first rotor, the procedure also comprises: inclusion, in the calculation of the aerodynamic velocity of each blade element of each rotor, of not only its own induced velocity but also that of the other rotor, to obtain a reference induced velocity v i p, resulting from the action of this secondary rotor prevailing at a specific point of the first rotor disc, defined by its coordinates (r ip, ψ ip), and filtering of this reference induced velocity v i p.