Resumen
A computer-aided method suitable for assisting in the design of an aircraft by providing a variable distribution V over an aircraf surface inside a predefined parameter space by means of a reconstruction of the results obtained through computations for an initial group of points in the parameter space using a CFD model comprising in each of said computations the following steps: a) Selecting relevant shock wave structures being defined by its thickness ´ sw , its position s sw and the variable jump V; b) Decomposing said variable distribution V into a smooth variable distribution V smooth and a shock wave variable distribution V jump corresponding to said relevant shock wave structures; c) Obtaining the variable distribution V at any point of the parameter space as a reconstruction of the smooth variable distribution V smooth and the shock wave variable distribution V jump obtained for said point.
Reivindicaciones
1. A computer-aided method suitable for assisting in the design or analysis of an aircraft by providing a variable distribution V over the surface of an aircraft or an aircraft component inside a predefined parameter space by means of a reconstruction of the results obtained through computations for an initial group of points in the parameter space using a CFD model in connection with a structured mesh defined on said surface, characterized in that in each of said computations it comprises the following steps: a) Selecting relevant shock wave structures along mesh lines in the chord direction taking place between a first point and a last point in the mesh line, being defined by its thickness δ<sw> , its position s<sw> in the mid point between said first point and said last point and the variable jump ΔV between the last and the first point; b) Decomposing said variable distribution V into a smooth variable distribution V<smooth> and a shock wave variable distribution V<jump> corresponding to said relevant shock wave structures; c) Obtaining the variable distribution V at any point of the parameter space as a reconstruction of the smooth variable distribution V<smooth> and the shock wave variable distribution V<jump> obtained for said point from the values obtained in step b). 2. A computer-aided method according to claim 1, characterized in that said step a) comprises the following sub-steps: a1) seeking for the maximum value ofdV /ds along said mesh line, being s the arc length measured from the leading edge of the aerodynamic surface and finding that it is larger than a first predetermined value P1; a2) setting the amplitude of the shock wave as the set of points around the point corresponding to the maximum value ofdV /ds wheredV /ds is larger than a second predetermined value P2 plus two additional points at each side; a3) considering said shock wave if the variable jump ΔV is greater than a third predetermined value P3. 3. A computer-aided method according to any of claims 1-2, characterized in that when only one shock wave is taken into account it is split into two shock waves with the same position s<sw> and thickness δ<sw> and with the variable jump ΔV equal to half the total value. 4. A computer-aided method according to any claims 1-3, characterized in that the shape of the shock wave variable distribution V<jump> is a linear shape. 5. A computer-aided method according to any claims 1-3, characterized in that the shape of the shock wave variable distribution V<jump> is a non-linear shape. 6. A computer-aided method according to any of claims 1-5, characterized in that said variable distribution V 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 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. 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.
