JF-22超高速风洞理论基础与关键技术

doi:10.7527/S1000-6893.2024.31130

Abstract

Abstract:

The assessment of hypersonic flight technology at home and abroad always relies on flight tests， which are time-consuming and expensive， and have posterior risks. The development of advanced hypersonic ground test facilities has been a fundamental research topic in aerodynamics frontier for decades； however， the existing test facilities are still inadequate for the required technology development of air-breathing hypersonic engines at high Mach numbers. The successful development of the JF-22 hypervelocity wind tunnel under the National Major Scientific Research Instrument Project supported by the National Natural Science Foundation of China is a major breakthrough in this area. This paper first reviews the research background of the hypersonic wind tunnel and introduces the four basic requirements of the wind tunnel based on engineering practice. Considering thermo-chemically reacting gas flows， the necessity of revolutionary change of the wind tunnel test simulation criteria of experimental aerodynamics from “flow similarity simulation” to “flight condition reproduction” is discussed. Then， the theories and technologies for detonation-driven hypervelocity shock tunnels are systematically expounded， and the engineering problems solved with the theories and technologies are also discussed. Finally， the technology system of the JF-22 hypervelocity wind tunnel， developed on the basis of these theories is summarized and evaluated with the JF-22 calibration results. These results not only verify the theories of detonation-driven hypervelocity shock tunnel， but also show a comprehensive assessment of the JF-22’s technology system. The success of the JF-22 hypervelocity wind tunnel is a new milestone in developing advanced hypersonic test facilities. The JF-22 remarkable performances， such as high flow velocity， high total temperature and high stagnation pressure， and wide speed range and altitude are of significance for supporting the research on air-breathing hypersonic engines， aerospace aircrafts， and the frontier of high-temperature gas dynamics.

Key words: forward detonation driver, chemically-reacting gas flow, hypervelocity shock tunnel, shock expansion acceleration, air-breathing hypersonic engine, aerospace vehicle

CLC Number:

V211.7

Zonglin JIANG, Guilai HAN, Yunpeng WANG, Yunfeng LIU, Chaokai YUAN, Changtong LUO, Chun WANG, Zongmin HU, Meikuan LIU. Theoretical bases and key technologies of JF-22 hypervelocity wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(5): 531130.

Figures/Tables 14

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Theoretical bases and key technologies of JF-22 hypervelocity wind tunnel

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