A high-enthalpy shock tunnel flow field diagnosis device and method

By employing a nested double-layered square tube structure and various measurement methods, the problem of measuring flow field parameters in high-enthalpy shock wind tunnels has been solved, enabling accurate measurement of flow field parameters in high-enthalpy shock wind tunnels and supporting aerodynamic and aerothermal characteristic tests of hypersonic vehicles.

CN122448474APending Publication Date: 2026-07-24CHINA AERODYNAMICS RES AND DEV CENT ULTRA-HIGH SPEED AERODYNAMICS RES INST
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
CHINA AERODYNAMICS RES AND DEV CENT ULTRA-HIGH SPEED AERODYNAMICS RES INST
Filing Date
2026-06-29
Publication Date
2026-07-24

AI Technical Summary

Technical Problem

Quantifying the flow field parameters in high-enthalpy shock tunnels is difficult, especially under high temperature and high pressure conditions where flow field parameter measurements are inaccurate. The hydrogen-oxygen combustion reaction is complex, the test time is short, and the flow field parameters are difficult to determine.

Method used

It adopts a double-layer square tube structure with inner and outer nesting. The inner square tube has a hollow flow channel in the center, and the outer square tube has an outer baffle and optical window at the front. Combined with pressure sensor, TDLAS measurement unit and schlieren system, it measures parameters such as flow field density, velocity and temperature.

Benefits of technology

It enables accurate measurement of flow field parameters in high-enthalpy shock tunnels, provides an efficient flow field diagnostic method, and supports aerodynamic and aerothermal characteristic tests of hypersonic vehicles.

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Abstract

The present application belongs to the technical field of wind tunnel test, and discloses a high-enthalpy shock tunnel flow field diagnosis device and method. The main body of the flow field diagnosis device is a double-layer square tube structure embedded inside and outside. The inner layer center cavity is an inner flow channel, and a 16° wedge is fixed in the inner flow channel. The front section of the outer layer square tube body is provided with an outer baffle, and the rear section is a straight section. The double-layer square tube structure corresponding to the 16° wedge is provided with left-right symmetrical optical windows, and the flow field density change of the 16° wedge is observed through a schlieren system. The front section of the outer layer square tube body is provided with a TDLAS measurement unit, the rear section is provided with a ball head stagnation point heat flow assembly and a pitot pressure assembly. The flow field diagnosis method comprises installing the flow field diagnosis device, performing flow field measurement test, and calculating flow field parameters. The flow field diagnosis device and method are verified by multiple test means, and the free stream parameters of the high-enthalpy shock tunnel are given, thereby providing technical support for developing hypersonic aircraft aerodynamic force and aerodynamic heat characteristic test and air-breathing power characteristic evaluation test.
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