A high-speed wind tunnel test simulation method for large-scale grid rudder

Abstract

The invention relates to a high-speed wind tunnel test simulation method for a large-scale grid rudder. According to the original large-slenderness grid rudder model, three scale models satisfying the wind tunnel test conditions are established, which are truncated grid rudders respectively. model, a gridless rudder truncated model, and a full-scale scaled gridless rudder model; the three scaled models were placed in a wind tunnel for simulation tests, and the balance system used was unified to ensure measurement accuracy; passed The wind tunnel test obtains the test data of the three models, and processes the test data to finally obtain the data of the original model. The present invention designs a truncated model with a grid rudder for a grid rudder model with a large slenderness ratio and a long straight section, and gives priority to ensuring the model size of the grid rudder, and at the same time, the model length meets the requirements of the wind tunnel test. The aerodynamic characteristics of the front and rear grid rudders are basically unchanged, effectively solving the processing problems and structural strength problems encountered in the large-scale scale grid rudder model.

Description

technical field [0001] The invention belongs to the field of experimental aerodynamics and relates to a high-speed wind tunnel test simulation method for a large-scale grid rudder. Background technique [0002] Generally, when the large-scale grid rudder model is used for supersonic wind tunnel tests, due to the large load of the grid rudder and the thin wall of the grid, if the scale is the same as that of the missile body, that is, the belt is designed according to a completely geometrically similar scale. The wind tunnel test model of grid rudder often encounters the following problems: [0003] (1) The thickness of the grid wall after scaling is very small, and some are even less than 0.1mm, which brings many difficulties to the model processing, and is even difficult to realize in the processing technology; [0004] (2) Due to the large load, the strength and stiffness of the scaled-down grid rudder are very weak, which basically cannot meet the requirements of the hig...

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Problems solved by technology

[0003] (1) The thickness of the grid wall after scaling is very small, and some are even less than 0.1mm, which brings many difficulties to the model processing, and is even difficult to realize in the processing technology;

[0004] (2) Due to the large load, the strength and stiffness of the scaled-down grid rudder are very weak, which basically cannot meet the requirements of the high-speed transient wind tunnel test. The model is easily damaged in the high-speed airflow, especially when the wind tunnel is started. The impact of the airflow on the model caused damage to the grid rudder, resulting in the failure of the test;

[0005] (3) After the model is scaled down, the difference between the boundary layer effect and the actual model causes the simulation of aerodynamic characteristics to be distorted, and even due to the small spacing between the grids, the airflow is blocked, and the aerodynamic characteristics of the aircraft cannot be truly simulated

After comparative analysis of experiments, it is found that the thickening of the grid wall has little effect on the normal force, but the increase of resistance is more obvious

Especially at low supersonic speed, the thickening of the grid wall reduces the flow area of ​​the grid rudder, which is prone to airflow congestion, and a strong detachment shock wave is formed in front of the grid rudder, resulting in a sharp increase in resistance and a forward movement of the center of pressure , the test data is seriously distorted

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