An automatic trimming method for two-dimensional airfoil numerical simulation

Abstract

The invention discloses an automatic trimming method for two-dimensional airfoil numerical simulation, which is characterized by comprising the following steps: S1, generating an original calculation grid of the two-dimensional airfoil; the original calculation grid includes splicing grid blocks; S2, read the space point coordinates and boundary conditions of the original calculation grid, and perform numerical simulation on the spliced ​​grid block according to the read space point coordinates and boundary conditions, and obtain the pitch moment coefficient under the current declination angle of the elevator surface; S3, According to the pitch moment coefficient at the current elevator surface declination angle, it is judged whether the elevator surface has reached the trim state. If the elevator surface has not reached the trim state, adjust the declination angle of the elevator surface, and repeat steps S2 to S3 until the trim state is reached. The invention realizes the automatic trimming of the deflection angle of the elevator rudder surface through numerical simulation of the splicing grid blocks of the two-dimensional airfoil, and the whole process does not require manual intervention, which is convenient and quick.

Description

technical field [0001] The invention relates to the field of surface and space grid generation in computational fluid dynamics, in particular to an automatic trimming method for two-dimensional airfoil numerical simulation. Background technique [0002] In Computational Fluid Dynamics (CFD), it is of great engineering significance to obtain the aerodynamic characteristics of a two-dimensional airfoil in the trim state (zero pitch moment) at different Mach numbers and different angles of attack. The two-dimensional airfoil can keep the pitching moment zero by the deflection of the elevator surface, but under different Mach numbers and different angles of attack, the deflection angle of the elevator surface to satisfy the trim state of the airfoil is different, which needs to be added in the calculation iteration process of CFD. Sure. This requires a method of rapid object surface deformation and automatic generation of computational grids to simulate different elevator surfa...

AI Technical Summary

Problems solved by technology

At present, for the mainstream structural grid method, due to the inherent geometric properties of the structural grid that are difficult to automatically generate, there is no related automatic balancing technology in the CFD field.

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