Sensitivity analysis method considering shock waves

Abstract

The invention relates to the field of sensitivity problem research, and discloses a sensitivity analysis method considering shock waves, which is realized through the following steps of: 1, performingshock wave interference analysis on incoming flow disturbance waves to obtain new disturbance waves generated after shock wave interference; 2, analyzing the obtained new disturbance wave, dividing regions according to an analysis result, and then researching the situation that the new disturbance wave in each region excites the disturbance wave of the boundary layer; and 3, analyzing a mechanismof exciting boundary layer disturbance waves by new disturbance waves in each region. According to the method, the existence of flow field shock waves is considered, a numerical calculation and theoretical analysis method is utilized, disturbance is tracked from incoming flow to shock waves, the shock waves are propagated downstream to enter a boundary layer, finally, the evolution process of unstable waves is excited, and the sensitivity mechanism and propagation path of incoming flow disturbance in the whole process can be meticulously studied.

Description

technical field [0001] The invention relates to the study of susceptibility problems, in particular to a susceptibility analysis method considering shock waves. Background technique [0002] When the airflow blows over an object in nature, a thin layer of adhesion is formed on the surface due to the viscosity of the gas, which is called the boundary layer. Boundary layer flow has two states: laminar flow and turbulent flow. Compared with laminar flow, turbulent flow has the characteristics of high friction, high heat flow, and strong mixing, and is very destructive to objects (such as aircraft). The transition from laminar to turbulent flow is called a transition. If an effective transition prediction technique can be established to predict the position of the boundary layer transition, the thermal protection design of the aircraft can be better carried out. [0003] To establish the transition prediction technology, it is necessary to understand the transition problem sci...

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Problems solved by technology

However, in practice, due to the role of the front end of the model, there are oblique shock waves or bow shock waves in the flow field, which will change the disturbance form, propagation path, and the efficiency of exciting boundary layer disturbance waves when the incoming flow disturbance enters the boundary layer

[0007] (2) Insufficient understanding of disturbance information after shock wave

Numerical calculations can simulate the entire receptive process of the incoming flow disturbance passing through the shock wave and even stimulating the boundary layer disturbance, but the form of disturbance after the shock wave has not yet been understood, which is not conducive to the study of its mechanism of stimulating the downstream boundary layer disturbance

[0008] (3) Insufficient understanding of the evolution and excitation process of the post-shock disturbance

In the past, numerical calculations only analyzed the process of downstream excitation of the boundary layer disturbance, and there was a blind spot in the understanding of the evolution process of the disturbance from the shock wave to the boundary layer

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