Incoming flow change induced unsteady simulation method and system, storage medium and terminal

Abstract

The invention discloses an incoming flow change induced unsteady simulation method and system, a storage medium and a terminal, and the method comprises the steps: generating a computational grid at an initial moment based on the shape of an aircraft; calculating a steady flow field of the aircraft at the initial moment; calculating an unsteady flow field when incoming flow parameters change; carrying out discretization and linearization processing on the unsteady three-dimensional Navier-stockes equation set; calculating the value of the left-end item LHS at the n+1 moment; updating the incoming flow parameter reference quantity at the n+1 moment; calculating according to the reference value at the current moment, calculating according to the reference value at the (n+1) moment, and calculating the reference value at the previous moment; calculating a dimensionless time step length at the moment (n+1); and calculating the RHS value of the right-end item. The aerodynamic unsteady effect induced by incoming flow parameter change is considered, a general universal formula for calculating the RHS of the right-end item is adopted, and based on theoretical derivation, the program modification amount is small, and the calculation amount is small.

Description

[0001] The invention relates to the field of fluid mechanics, in particular to an unsteady simulation method, system, storage medium and terminal induced by incoming flow changes. Background technique [0002] The variation of incoming flow parameters widely exists in the simulation of aircraft motion process, and has a wide range of application requirements in the aerospace field. At present, the numerical simulation process of the change of incoming flow parameters generally only considers the change of the parameter itself, and does not consider the additional unsteady effects after the change of the parameter, such as figure 1 As shown, there is a certain error between the aerodynamic force obtained by the numerical simulation and the real flight process. [0003] Therefore, in this field, how to provide a theoretically deduced introduction process of unsteady effects, based on the dual time step method, elaborates in detail how to modify the original dual time step method...

AI Technical Summary

Problems solved by technology

At present, the numerical simulation process of the change of incoming flow parameters generally only considers the change of the parameter itself, and does not consider the additional unsteady effects after the change of the parameter, such as figure 1 As shown, there is a certain error between the aerodynamic force obtained by the numerical simulation and the real flight process

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