Turbulence model for prediction of high Mach number intensive shock wave flow field aerodynamic heat and building method of turbulence model

Abstract

The invention discloses a turbulence model for prediction of high Mach number intensive shock wave flow field aerodynamic heat and a building method of the turbulence model, and belongs to the field of design of a hypersonic velocity flight vehicle thermal protection system. The method comprises the steps of firstly adopting a dimensionless pressure to calculate a smooth factor of a grid node (I,J,K); calculating an attenuation function value of the grid node, and determining a strong discontinuous area in a flow field; making an attenuation function coupled to a k-OmegaSST turbulence model to build the turbulence model for the prediction of the high Mach number intensive shock wave flow field aerodynamic heat. Compared with an existing shock wave discontinuous detection method and an existing turbulence model, the intensive shock wave discontinuous detection method which is put forward based on a smooth factor conception can achieve automatic detection even aiming at a complicated outline blunt body flight vehicle; the attenuation function is combined with the k-OmegaSST turbulence model to achieve high-precision aerodynamic heat prediction and simulation, the calculating precision is obviously improved, and the error can be lowered to the range within 10%; the turbulence model for the prediction of the high Mach number intensive shock wave flow field aerodynamic heat and the building method of the turbulence model are high in practicability, and it is easy for the turbulence model to be fused into a modern parallelization CFD calculation program.

Description

technical field [0001] The invention belongs to the field of thermal protection system design for hypersonic aircraft, and in particular relates to a turbulence model that can be used for aerothermal prediction of high Mach number strong shock wave flow field. Background technique [0002] Hypersonic vehicles in near space have become the main goal of the aerospace technology development programs of world powers. Due to the long-term hypersonic flight of this type of aircraft, serious aerodynamic heating problems will occur. Therefore, the design of the aircraft thermal protection system has become a key technical difficulty in the development of hypersonic aircraft. Accurately predicting the aerodynamic thermal environment of the aircraft can not only significantly improve the effectiveness of the thermal protection system, but also increase the payload of the aircraft to a certain extent. [0003] When a hypersonic vehicle flies in a denser atmosphere, the hypersonic flow...

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Problems solved by technology

However, because the model proposed by Sinha et al. introduces non-local variables such as boundary layer thickness that need to be integrated, the modified turbulence model proposed by them is only suitable for the prediction and simulation of simple shape flow fields, and it is difficult to apply to modern hypersonic complex shapes. aircraft

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