Abstract: The present invention provides 2-phenylpiperazine derivatives having a benzofuran-2-yl group which contributes to increase the antiviral activity as well as, for some substituents, the CC50, giving more active and less cytotoxic compounds. Although further optimization and characterization of their mechanisms of action will be required for these compounds, they represent strong hit candidates for the development of a new class of antiviral compounds.

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 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 assisting in the design of an aircraft by providing the values of dimensional variables, dependant of a predefined set of parameters, for the complete aircraft or an aircraft component, comprising the following steps: a) Defining a parametric space grid; b) Obtaining a suitable Reduced Order Model (ROM) model, particularly a Proper Orthogonal Decomposition (POD) model, for calculating said variables for whatever point over the parametric space through an iterative process. Computer Fluid Dynamics (CFD) is used to calculate said variables for an appropriately selected set of points over the parametric space, which are used to approximate, via ROM and ad hoc interpolation, the variables in any other point over the parametric space. The method minimizes the required number of CFD calculations (to minimize the computational cost, which dramatically depends on this number) for a given level of error.

Abstract: A computer-aided method suitable for assisting in the design of an aircraft by providing the dimensioning aerodynamic forces and other relevant values comprising the following steps: a) Selecting a set of parameters of the aircraft, being said aerodynamic forces and other relevant values dependant of said parameters; b) Performing flow field CFD RANS computations for a number N1 of different combination of values of said parameters; c) Obtaining said aerodynamic forces and other relevant values for whatever combination of values of said parameters through a reduced-order model, generated by computing the POD modes of the flow variables, expanding the flow variables using said POD modes and obtaining the POD coefficients of said expanded flow variables using a genetic algorithm that minimizes the error associated to the expansion of the Navier-Stokes equations. The invention also refers to a system for carrying out said 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 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 the values of dimensional variables, dependant of a predefined set of parameters, for the complete aircraft or an aircraft component, comprising the following steps: a) Defining a parametric space grid; b) Obtaining a suitable Reduced Order Model (ROM) model, particularly a Proper Orthogonal Decomposition (POD) model, for calculating said variables for whatever point over the parametric space through an iterative process. Computer Fluid Dynamics (CFD) is used to calculate said variables for an appropriately selected set of points over the parametric space, which are used to approximate, via ROM and ad hoc interpolation, the variables in any other point over the parametric space. The method minimizes the required number of CFD calculations (to minimize the computational cost, which dramatically depends on this number) for a given level of error.

Abstract: A computer-aided method suitable for assisting in the design of an aircraft by providing the dimensioning aerodynamic forces and other relevant values comprising the following steps: a) Selecting a set of parameters of the aircraft, being said aerodynamic forces and other relevant values dependant of said parameters; b) Performing flow field CFD RANS computations for a number N1 of different combination of values of said parameters; c) Obtaining said aerodynamic forces and other relevant values for whatever combination of values of said parameters through a reduced-order model, generated by computing the POD modes of the flow variables, expanding the flow variables using said POD modes and obtaining the POD coefficients of said expanded flow variables using a genetic algorithm that minimizes the error associated to the expansion of the Navier-Stokes equations. The invention also refers to a system for carrying out said method.

Abstract: A system and a process for processing payments and transactions between payers (13) and payees (27, 29, 14, 14a, 13a, 46) associated to the system, using a first server (20) interconnected with telecommunication means (18, 19, 28, 47) with first data storage means (22) containing information on each associated payer (13) consisting of at least an admissible telephone number, at least a authorization criterion for authorizing a transaction, and a safety criterion associated to the admissible telephone number, as well as an admissible identification code of each payee; second data storage means (21) that contain a second information referring to the type of digital mobile telephone (16, 41) belonging to each telephone number; selecting means (20h) for verifying one of the telecommunication equipments (18, 19) that communicates with the digital mobile telephone (16, 41) identified by the admissible telephone number by means of a telecommunication service being compatible with the type of digital mobile tele