With the boom in deep space exploration by China since the beginning of the 21st century,the demand for high-enthalpy hypersonic shock tunnels has continued to increase.In this paper,three types of shock tunnels using...With the boom in deep space exploration by China since the beginning of the 21st century,the demand for high-enthalpy hypersonic shock tunnels has continued to increase.In this paper,three types of shock tunnels using free-piston,heated light-gas,and detonation drivers,respectively,are briefly summarized and compared.The development of large-scale hypersonic shock tunnels running in both backward and forward detonation driver modes is described in detail.A series of applications to hypersonic flow tests with engineering-scale test models demonstrate the success and advantages of this kind of shock tunnels.The challenges that arise in the operation of hypersonic tunnels are stressed,as are the requirements for precise measurement techniques in the harsh testing environments existing in these tunnels.A new approach for the development of next-generation detonation-driven high-enthalpy shock tunnels is recommended to address these challenges.展开更多
The hypersonic long-run scramjet test tunnel is one of the key ground facilities for the studies of ramjet/scramjet and hypersonic thermal management.Due to the significantly large heat loading,the nozzle of the tunne...The hypersonic long-run scramjet test tunnel is one of the key ground facilities for the studies of ramjet/scramjet and hypersonic thermal management.Due to the significantly large heat loading,the nozzle of the tunnel facility demands effective cooling protection.In this work,the two-dimensional,three-dimensional and axisymmetric Mach 6.5 nozzles at an inlet total temperature of 1840 K and a total pressure of 6.4 MPa were studied with main focuses on the properties of aerodynamic heating of nozzles.The present work aims to provide insights into the design of an effective cooling system for the nozzle and other components of the hypersonic long-run wind tunnel.展开更多
基金co-supported by the National Natural Sci-ence Foundation of China(Grant Nos.12172365,12072353,and 12132017)。
文摘With the boom in deep space exploration by China since the beginning of the 21st century,the demand for high-enthalpy hypersonic shock tunnels has continued to increase.In this paper,three types of shock tunnels using free-piston,heated light-gas,and detonation drivers,respectively,are briefly summarized and compared.The development of large-scale hypersonic shock tunnels running in both backward and forward detonation driver modes is described in detail.A series of applications to hypersonic flow tests with engineering-scale test models demonstrate the success and advantages of this kind of shock tunnels.The challenges that arise in the operation of hypersonic tunnels are stressed,as are the requirements for precise measurement techniques in the harsh testing environments existing in these tunnels.A new approach for the development of next-generation detonation-driven high-enthalpy shock tunnels is recommended to address these challenges.
基金supported by the National Natural Science Foundation of China(Grant Nos.11202218 and 11172309)
文摘The hypersonic long-run scramjet test tunnel is one of the key ground facilities for the studies of ramjet/scramjet and hypersonic thermal management.Due to the significantly large heat loading,the nozzle of the tunnel facility demands effective cooling protection.In this work,the two-dimensional,three-dimensional and axisymmetric Mach 6.5 nozzles at an inlet total temperature of 1840 K and a total pressure of 6.4 MPa were studied with main focuses on the properties of aerodynamic heating of nozzles.The present work aims to provide insights into the design of an effective cooling system for the nozzle and other components of the hypersonic long-run wind tunnel.
