A real-time simulation system of the effect of aerodynamic loads generated by the wake of a rotor of a hover-capable aircraft on the aircraft itself, comprising: - a cockpit seat for a pilot; - at least one simulated control device of said aircraft, which is able to receive a simulated command from said pilot to simulate a flight condition of said aircraft; - simulation means able to generate a simulated representation of said flight condition and perceptible from the cockpit seat; - a processing unit configured to receive a first signal associated with said command given via said control device in input and to generate and output a second control signal for said simulation means associated with said simulated aerodynamic loads; said simulation means comprising: - actuator means able to generate simulated aerodynamic loads on said cockpit seat; and - display means able to generate simulated visual indications that are visible from said cockpit seat; said processing unit comprising a storage unit in which aerodynamic data regarding said aircraft and said rotor is, in use, stored; characterized in that said processing unit is further configured to execute a cycle comprising the steps of: a) generating, with a given period (Δτ) and in a simulated flow field, a vortex ring with a radius (r) associated with the value of the disc circumference of said rotor and with a velocity circulation (Γ) proportional to the thrust of said rotor set by the pilot via said control device; b) associating a number of control points (A, B, C and D) to said vortex ring; c) computing the velocities induced on said control points (A, B, C and D) by the vortex ring and/or by at least some of the other vortex rings present in said simulated flow field and the asymptotic speed (Vasin) of the air with respect to said aircraft; d) moving said vortex ring according to said velocities induced on said control points (A, B, C and D); e) updating said vortex ring after said movement step; f) computing the velocity induced on at least one point of interest of said aircraft on the basis of the velocities induced on said control points (A, B, C and D) of said vortex rings present in the simulated flow field and said asymptotic speed (Vasin); g) calculating the consequent aerodynamic loads on said point of interest, once said velocity induced on said point of interest has been calculated, using said aerodynamic data stored in said storage unit; h) calculating the acceleration at said point of interest due to said aerodynamic loads present on the same said of point of interest; and i) generating said second control signal for said actuators and said display means on the basis of said acceleration on said point of interest of said aircraft. - a cockpit seat for a pilot; - at least one simulated control device of said aircraft, which is able to receive a simulated command from said pilot to simulate a flight condition of said aircraft; - simulation means able to generate a simulated representation of said flight condition and perceptible from the cockpit seat; - a processing unit configured to receive a first signal associated with said command given via said control device in input and to generate and output a second control signal for said simulation means associated with said simulated aerodynamic loads; - actuator means able to generate simulated aerodynamic loads on said cockpit seat; and - display means able to generate simulated visual indications that are visible from said cockpit seat; a) generating, with a given period (Δτ) and in a simulated flow field, a vortex ring with a radius (r) associated with the value of the disc circumference of said rotor and with a velocity circulation (Γ) proportional to the thrust of said rotor set by the pilot via said control device; b) associating a number of control points (A, B, C and D) to said vortex ring; c) computing the velocities induced on said control points (A, B, C and D) by the vortex ring and/or by at least some of the other vortex rings present in said simulated flow field and the asymptotic speed (Vasin) of the air with respect to said aircraft; d) moving said vortex ring according to said velocities induced on said control points (A, B, C and D); e) updating said vortex ring after said movement step; f) computing the velocity induced on at least one point of interest of said aircraft on the basis of the velocities induced on said control points (A, B, C and D) of said vortex rings present in the simulated flow field and said asymptotic speed (Vasin); g) calculating the consequent aerodynamic loads on said point of interest, once said velocity induced on said point of interest has been calculated, using said aerodynamic data stored in said storage unit; h) calculating the acceleration at said point of interest due to said aerodynamic loads present on the same said of point of interest; and i) generating said second control signal for said actuators and said display means on the basis of said acceleration on said point of interest of said aircraft.