Hypersonic mach-number-variable wind tunnel nozzle

Abstract

The invention discloses a hypersonic mach-number-variable wind tunnel nozzle which comprises two opposite pneumatic panels and two opposite lateral straight panels. A two-dimensional contracting-expanding passage is formed by the pneumatic panels and the lateral straight panels, and the two or one of the two pneumatic panels can rotate with outlet ends as shafts. The upper pneumatic panel and the lower pneumatic panel are used, so that airflow rotation angles of outlets are smaller, flow fields are symmetric, and proportion of an airflow core area is larger. In addition, without a complex control mechanism, the rotary nozzle is simpler in structure, and a sealing space and a cooling space are added. The hypersonic mach-number-variable wind tunnel nozzle has the advantages that mach-number variable range is wide, structure is simple, the flow fields are high-quality, the sealing space and the cooling space of the nozzle can be both considered, and the nozzle is high in adaptability, process and economy.

Description

technical field [0001] The invention relates to the field of hypersonic speed test wind tunnels, in particular to a hypersonic variable Mach number wind tunnel nozzle. Background technique [0002] The hypersonic wind tunnel is an indispensable ground equipment for hypersonic technology research. Its function is to simulate the airflow environment during hypersonic flight. The aerodynamic design goal is that the Mach number of the experimental section of the wind tunnel nozzle reaches the design Mach number. The Mach number of the section section is evenly distributed, and the airflow direction at the outlet of the nozzle is parallel to the axis of the wind tunnel; the design of the scheme also takes into account the applicability, manufacturability and economy of the nozzle. [0003] The hypersonic variable Mach number wind tunnel is a hypersonic wind tunnel in which the Mach number of the experimental airflow at the outlet of the wind tunnel nozzle and other state paramete...

AI Technical Summary

Problems solved by technology

The disadvantage of this method is that the Mach number range is limited, and the range of Mach number 4 to 7 requires 3 to 4 nozzle systems to complete, and the system structure is complex and the cost is high.

[0009] ②The semi-flexible two-dimensional nozzle scheme can ensure the uniformity of the wind tunnel flow field as much as possible, and the Mach number has a wide range of variation, but the aerodynamic profile control makes the nozzle structure and control process very complicated

[0010] ③Axisymmetric nozzle plug nozzle scheme, this method can achieve a large range of Mach number variation, but the existence of the central cone boundary layer has a great impact on the quality of the nozzle outlet flow field, resulting in a very unstable flow field. uniform

[0011] ④ The method of adding energy to the expansion section of the nozzle to control the Mach number and enthalpy value, but the nozzle material, microwave energy control and other technologies are still in the research process, and the realization technology is still immature

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