A Calculation Method for Aerodynamic Heating of Complex Aircraft Applicable to Engineering Design

Abstract

This method proposes a complex aircraft aerodynamic heating calculation method that can be used in engineering design. This method uses the CFD method to solve the Euler equation for the external inviscid flow field to calculate the complex shape; determine the outer edge parameters of the aircraft boundary layer through CFD; and then in Inside the boundary layer where the viscosity plays a dominant role, the engineering reference enthalpy method is used to calculate the surface heat flow, and various forms of the reference enthalpy method are synthesized. This method not only overcomes the disadvantage that the pure engineering algorithm is difficult to solve the complex shape and surface parameters, but also the calculation amount is much smaller than the pure numerical algorithm, which effectively improves the accuracy and calculation efficiency of the outer edge parameters of the aircraft boundary layer. This method and software use the CFD method to establish a surface flow field database for the complex shape of the aircraft, and can calculate the aerodynamic heating of the aircraft for a long time along the flight trajectory. The calculation efficiency is much higher than the direct numerical solution of the N-S equation to calculate the aerodynamic heat. It can be applied to engineering design.

Description

A kind of complex aircraft aerodynamic heating calculation method that can be used in engineering design Technical field The invention belongs to the overall technical field of missiles, and be specifically related to a kind of complex aircraft aerodynamic booster for engineering design thermal calculation method, Background technique [0002] Supersonic vehicle is flying at a high Mach number, and the temperature near the wall is very high. The high-temperature air continuously transfers heat to the wall surface, As a result, the shape of the aircraft is ablated, and the structural strength and rigidity are changed, which seriously affects the normal flight of the aircraft. superb The sonic aerothermal problem is one of the key technologies in the development of hypersonic vehicles. For a long time based on the aerodynamic heating engineering calculation method of components, for the aircraft of complex shape, including axisymmetric, Various lifting bodies such as p...

AI Technical Summary

Problems solved by technology

CFD (Computational Fluid Dynamics) calculation methods to predict the thermal environment of hypersonic vehicles, but these calculation methods are complex

And the calculation efficiency is low, and the requirements for computer resources are very high. At present, it is only used for simple shapes or single-time point steady states.

published research results, it is difficult to be applied in the design of engineering units

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