Patent ID: 9187187
Filing Date: 2015-11-17
Classification: B64F,G01M,G06F,Y02T

Abstract:
1. A method for simulating aerodynamic flow around an aircraft, so as to determine aerodynamic loads exerted on said aircraft, the loads being dependent on trim of a given structural element of the aircraft, the method determining an aerodynamic model of the aircraft for a plurality of aerodynamic flow scenarios, the method comprising determining the aerodynamic model by determining global dynamic pressure QA exerted around the structural element by a process including the following steps: (a) employing a mesh produced around the overall shape of the aircraft, (b) simulating the aerodynamic flow around the aircraft by employing said mesh, (c) determining local dynamic pressure qA around the surface of said structural element, and (d) calculating the global dynamic pressure QA around the surface of the structural element, in the presence of the aeroplane without said structural element, on the basis of the local dynamic pressure qA, wherein the global dynamic pressure QA enables determination of an aerodynamic pressure force F exerted on the overall surface of the structural element. (e) generating the aerodynamic model in accordance with steps (a)-(d).