METHOD AND TOOL FOR SIMULATING THE AERODYNAMIC BEHAVIOR OF AERODYNAMIC ELEMENT OF AN AIRCRAFT HAVING A VARIABLE ARRAY ANGLE

摘要

The invention relates to a computer simulation method suitable for obtaining the aerodynamic behaviour of an aerodynamic element of an aircraft in a flow, said aerodynamic element having, between the leading edge and the trailing edge thereof, a local sweep angle with a value that varies between a value of the leading edge and a value of the trailing edge.