Abstract: A computer-aided method suitable for assisting in the design of an object zone, such as a CROR engine of an aircraft subjected to high vorticity and/or low static pressure fields when moving inside a flow field, by providing suitable seed points for constructing vortex core lines in a fluid data model of the environment of the object zone and a system based on the method. The method steps are: a) Obtaining a dataset containing all the cells or points satisfying one of the conditions of four Region-based vortex detection criteria (the Q-criterion, the Kinematic vorticity number, the ?-criterion, the ?2-criterion); b) Obtaining a new dataset containing all the cells or points of the previous dataset satisfying one of the conditions mentioned in step a) not selected previously; c) Repeating the step b) until all the conditions mentioned in step a) have been selected in step b).

Abstract: A computer-aided method suitable for assisting in the design of an object zone such as a CROR engine of an aircraft subjected to high vorticity and/or low static pressure fields when moving inside a flow field by providing suitable seed points for constructing vortex core lines in a fluid data model of the environment of said object zone and a system based in said method. The method steps are: a) Obtaining a dataset of candidate seeds containing all the cells or points satisfying a condition of the pressure gradient in the direction of the flow or a condition of the drag friction coefficient at the solid boundaries; b) Updating the previous dataset of candidate seeds with all the cells or points satisfying the equation not used for obtaining the dataset in step a).

Abstract: A computer-aided method suitable for assisting in the design of an aircraft by providing relevant dimensioning values corresponding to an aircraft component in transonic conditions inside a predefined parameter space by means of a reconstruction of the CFD computations for an initial group of points in the parameter space using a POD reduced-order model, comprising the following steps: a) Decomposing for each flow variable the complete flow field into a smooth field and a shock wave field in each of said computations; b) Obtaining the POD modes associated with the smooth field and the shock wave field considering all said computations; c) Obtaining the POD coefficients using a genetic algorithm (GA) that minimizes a fitness function; d) Calculating said dimensioning values for whatever combination of values of said parameters using the reduced-order model. The invention also refers to a system able to perform the method.

Abstract: A method of improving a 2D or 3D multiblock-structured mesh of an object that moves through a fluid medium, such as an aircraft. The method is used in the design of the object in connection with a defined analytical scheme, the mesh having been generated with rectangular (2D) or hexahedral (3D) blocks under constraints that may cause the mesh to include irregular blocks comprising the following steps: finding irregular blocks in the mesh; degenerating the irregular blocks merging contiguous edges or sides in one edge or side so that triangular (2D) or pentahedral (3D) blocks are formed and extending the modifications all along the blocks that are propagated; and generating several rectangular (2D) or hexahedral (3D) regular blocks inside the triangular (2D) or pentahedral (3D) blocks. A system for carrying out the method.

Abstract: A computer-aided method suitable for assisting in the design of an aircraft by providing a variable distribution V over an aircraft 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 Sswand the variable jump ?V; b) Decomposing said variable distribution V into a smooth variable distribution Vsmooth and a shock wave variable distribution Vjump 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 Vsmooth and the shock wave variable distribution Vjump obtained for said point.

Abstract: A computer-aided method suitable for calculating the position of a mobile surface of an object such an aircraft that moves through a fluid medium, which is affected by at least an upstream or downstream object component, for achieving a predetermined value Vo of a predetermined object performance target, including the following steps: preparing a computer-implemented CFD model of the object having said mobile surface in a first position; solving the CFD model and obtaining the value Vi of said object performance target; if the difference between Vi and Vo is greater than a predetermined value, modifying the CFD model changing the position of the mobile surface in the CFD model and iterating the solving step. The invention also refers to a system for carrying out the method.

Abstract: A method of generating a mesh of an object (11) that moves through a fluid medium which is used in the design or analysis of the object (11) in connection with a hybrid method combining RANS and LES comprising the following steps: a) creating an inner “C” topology (21) around the object (11) for a boundary layer description; b) creating an outer “C” topology (23) covering a space region including the separation region; c) locating the separation region and adapting to it the inner and outer “C's” topologies (21, 23) so that the outer “C” topology (23) is adapted to the size of the separated region and the inner “C” topology (21) is adapted to the size of the boundary layer; d) refining the mesh in the separation region according to the specifications of the RANS/LES method. The invention also provides a system for carrying out the method.

Abstract: A computer-aided method suitable for assisting in the design of an aircraft by providing relevant dimensioning values corresponding to an aircraft component in transonic conditions inside a predefined parameter space by means of a reconstruction of the CFD computations for an initial group of points in the parameter space using a POD reduced-order model, comprising the following steps: a) Decomposing for each flow variable the complete flow field into a smooth field and a shock wave field in each of said computations; b) Obtaining the POD modes associated with the smooth field and the shock wave field considering all said computations; c) Obtaining the POD coefficients using a genetic algorithm (GA) that minimizes a fitness function; d) Calculating said dimensioning values for whatever combination of values of said parameters using the reduced-order model. The invention also refers to a system able to perform the method.

Abstract: A computer-aided method suitable for assisting in the design of an aircraft by providing a variable distribution V over an aircraft 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 ssw and the variable jump ?V; b) Decomposing said variable distribution V into a smooth variable distribution Vsmooth and a shock wave variable distribution Vjump 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 Vsmooth and the shock wave variable distribution Vjump obtained for said point.

Abstract: A computer-aided method for adapting a multi-block mesh topology of an object (11) to a modification in its geometry resulting from an operation defined in respect to some spatial directions, the method being used in the design of said object (11) by means of numerical simulation in structured meshes, comprising the following steps: a) providing the starting geometry (21) and mesh topology description (31); b) finding key points (25); c) finding the set of key vertexes placed at said key points (25); d) finding all the reference vertexes seeking for the vertexes connected to the key vertexes along said spatial directions; e) performing the geometrical operation and obtaining the adapted mesh topology moving said set of key vertexes to the position determined by the modified geometry (23) and the rest of vertexes proportionally to the displacement of the corresponding key vertex. The invention also refers to a system for carrying out said method.

Abstract: A method of generating a mesh of an object (11) that moves through a fluid medium which is used in the design or analysis of said object (11) in connection with a hybrid method combining RANS and LES comprising the following steps: a) creating an inner “C” topology (21) around said object (11) for a boundary layer description; b) creating an outer “C” topology (23) covering a space region including the separation region; c) locating the separation region and adapting to it said inner and outer “C's” topologies (21, 23) so that the outer “C” topology (23) is adapted to the size of the separated region and the inner “C” topology (21) is adapted to the size of the boundary layer; d) refining the mesh in the separation region according to the specifications of said RANS/LES method. The invention also refers to a system for carrying out said method.

Abstract: A computer-aided method suitable for calculating the position of a mobile surface of an object such an aircraft that moves through a fluid medium, which is affected by at least an upstream or downstream object component, for achieving a predetermined value Vo of a predetermined object performance target, comprising the following steps: preparing a computer-implemented CFD model of said object having said mobile surface in a first position; solving said CFD model and obtaining the value Vi of said object performance target; if the difference between Vi and Vo is greater than a predetermined value, modifying the CFD model changing the position of the mobile surface in the CFD model and iterating the solving step. The invention also refers to a system for carrying out said method.

Abstract: A method of improving a 2D or 3D multiblock-structured mesh of an object that moves through a fluid medium, such as an aircraft, which is used in the design of said object in connection with a defined analytical scheme, said mesh having being generated with rectangular (2D) or hexahedral (3D) blocks under constrains that may cause that the mesh include irregular blocks (31) comprising the following steps: finding irregular blocks (31) in the mesh; degenerating said irregular blocks (31) merging contiguous edges or sides (33, 35) in one edge or side (37) so that triangular (2D) or pentahedral (3D) blocks (41) are formed and extending the modifications all along the blocks that are propagated; generating several rectangular (2D) or hexahedral (3D) regular blocks (43, 45, 47) inside said triangular (2D) or pentahedral (3D) blocks (41). The invention also refers to a system for carrying out said method.