Design method of special pressure measuring rake for deformed flow channel of wing-body fusion aircraft ventilation model

Abstract

The invention discloses a design method of a special pressure measurement rake for a deformed flow channel of a wing-body fusion aircraft ventilation model. The design method of the pressure measurement rake obtains the deformation of the deformed internal flow channel under the interaction between the internal flow of the internal flow channel and the external flow of the model through a numerical simulation method. Flow characteristics, according to the numerical simulation results, the measurement section is divided into sub-regions, and the area of ​​the sub-region is used as the weight of the internal flow parameters of each sub-region to determine the number and position of the total pressure measurement points and static pressure measurement points on the measurement section The rake body was designed to reduce the effect of blocking interference. Through the above process, a special pressure measuring rake suitable for the deformed inner flow channel of the aircraft ventilation test model with fused wing body layout was designed.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a design method for a special pressure measuring rake for a deformed flow channel of a wing-body fusion aircraft ventilation model. Background technique [0002] When a fluid such as air or water flows over the surface of an object, there is always a thin layer of uneven velocity distribution near the surface of the object, which is called the boundary layer. In the region inside the boundary layer, the fluid viscosity plays a dominant role; in the region outside the boundary layer, the influence of fluid viscosity is weak. The research results show that the flow characteristics of the inner region of the boundary layer have an important impact on the entire space flow field, and are related to the optimization of the layout schemes of the buried weapon bay and the aircraft inlet and the improvement of equipment performance. Therefore, the flow characteristi...

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Problems solved by technology

[0005] At present, the design method of pressure measurement rakes in domestic high-speed wind tunnels is established for conventional layout aircraft, resulting in the traditional conventional pressure measurement rakes with simple shape and regular shape, and the number of measurement points is small and symmetrically distributed.

For the new generation of aircraft with wing-body fusion layout design, the internal flow channel is deformed, the cross section is irregular, the flow is asymmetrical, and the total pressure distribution at the outlet is quite different. The traditional pressure rake cannot meet its high-speed wind tunnel test. need

[0006] The shortcomings are mainly reflected in: ①The traditional symmetrical pressure measuring rake has a low matching degree with the irregular flow of the deformed inner flow channel of the wing-body fusion aircraft, and it is difficult to accurately obtain the pressure distribution near the outlet, resulting in relatively large errors in the calculation results of internal resistance. ②In order to improve the measurement accuracy, the pressure measurement points are encrypted on the traditional pressure measurement rake, which will lead to serious blockage and interference of the pressure measurement rake, and the test results cannot truly reflect the flow characteristics of the inner flow channel; ③In the later data processing process, the traditional pressure measurement The calculation weight of each total pressure measurement point on the rake is the same, it is difficult to reflect the contribution of the total pressure difference at different positions to the internal resistance, and the accuracy of the test results is affected

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