Air inlet front edge shock wave aerodynamic heat simulation analysis method

Abstract

The air inlet channel leading edge shock wave aerodynamic heat simulation analysis method comprises the steps: S1, enabling simulation molecules to carry out constant-speed linear motion with the duration being delta tm at the current speed and in the current direction; s2, simulating the action with the boundary in the molecular motion process, and adopting different processing methods for different boundaries; s3, sorting the simulation molecules according to the grid serial numbers; s4, sampling the molecular collision pairs; s5, determining molecular energy distribution before collision, determining a molecular energy relaxation process during collision, and determining redistribution of internal energy after molecular collision according to the intramolecular energy transfer model; s6, simulating a chemical reaction of the sampled molecular collision pairs to obtain thermodynamic state parameters of each molecular collision pair; s7, repeating the steps S1-S6, judging whether thesimulation time reaches the sampling time or not after N time steps, if so, entering S8, and otherwise, repeating the steps S1-S7; and S8, performing statistical calculation on the simulation molecules in each grid unit to obtain a temperature field of the shock waves at the front edge of the air inlet channel.

Description

technical field [0001] The invention relates to a method for aerodynamic thermal analysis of shock wave at the leading edge of an inlet, in particular to an aerothermal simulation method for shock wave aerodynamic and thermal analysis at the leading edge of an inlet when an aircraft flies at a high Mach number. Background technique [0002] When the aircraft flies at a high Mach number (Ma>5), the gas at the leading edge of the inlet is a hypersonic flow, and the rapid change of flow velocity from the free flow to the wall of the inlet of the aircraft causes a strong bow-shaped excitation around the leading edge of the inlet. Wave. In addition to the heat generated by the friction between the incoming air and the aircraft cabin, the bow shock wave will also generate strong aerodynamic heat. The temperature of the flow field at the leading edge of the inlet of a hypersonic aircraft is close to 2000K. Such high temperature conditions will bring great challenges to the ther...

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Problems solved by technology

Such high temperature conditions will bring great challenges to the thermal protection of aircraft bulkheads

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