Zobrazeno 1 - 10
of 13
pro vyhledávání: '"Junmou Shen"'
Publikováno v:
Aerospace, Vol 10, Iss 5, p 455 (2023)
High enthalpy stagnation gas can be converted into hypervelocity flow through the contraction—expansion nozzle. The enthalpy flow in the nozzle can be divided into three regions: an equilibrium region, a non-equilibrium region, and a frozen region.
Externí odkaz:
https://doaj.org/article/64e64174e539452094c603e2ed8d828e
Publikováno v:
Advances in Aerodynamics, Vol 2, Iss 1, Pp 1-20 (2020)
Abstract The high enthalpy nozzle converts the high enthalpy stagnation gas into the hypervelocity free flow. The flow region of the high enthalpy nozzle consists of three parts: an equilibrium region upstream of the throat, a non-equilibrium region
Externí odkaz:
https://doaj.org/article/f54b0e54a1ab405ea65b696027fdf00a
Publikováno v:
Chinese Journal of Aeronautics, Vol 32, Iss 11, Pp 2422-2432 (2019)
In supersonic wind tunnels, the airflow at the exit of a convergent-divergent nozzle is affected by the connection between the nozzle and test section, because the connection is a source of disturbance for supersonic flow and the source of disturbanc
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::b98bb8e3cc6b4d85e285469b0f01343f
https://doi.org/10.1016/j.cja.2019.07.005
https://doi.org/10.1016/j.cja.2019.07.005
The high enthalpy shock tunnel can simulate the free-flow speed above 3km/s. The characteristic of the flow is that the kinetic energy of the high enthalpy stagnation gas is high enough to effectuate high-temperature effects such as dissociation even
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::6d6214c13b734a1673b8eec637e69029
https://doi.org/10.21203/rs.3.rs-64862/v1
https://doi.org/10.21203/rs.3.rs-64862/v1
Publikováno v:
Advances in Aerodynamics, Vol 2, Iss 1, Pp 1-20 (2020)
The high enthalpy nozzle converts the high enthalpy stagnation gas into the hypervelocity free flow. The flow region of the high enthalpy nozzle consists of three parts: an equilibrium region upstream of the throat, a non-equilibrium region near the
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::e54549e20ce6cdb296aca8851e283be7
https://doi.org/10.21203/rs.3.rs-20739/v3
https://doi.org/10.21203/rs.3.rs-20739/v3
Autor:
Li Chen, Hongbo Lu, Zhang Bingbing, Chen Xing, Bi Zhixian, Junmou Shen, Nong Chen, Yi Xiangyu
Publikováno v:
Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019).
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::730ab8744d379156e4c862421ee0f96e
https://doi.org/10.3850/978-981-11-2730-4_0441-cd
https://doi.org/10.3850/978-981-11-2730-4_0441-cd
Publikováno v:
Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019).
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::13683fd6e6ff27559aeca58221bf73ba
https://doi.org/10.3850/978-981-11-2730-4_0443-cd
https://doi.org/10.3850/978-981-11-2730-4_0443-cd
Publikováno v:
31st International Symposium on Shock Waves 2 ISBN: 9783319910161
The running time of the hypersonic Ludwieg tube quiet wind tunnel is very important to simulate the quiet flow field in the test section, which could contribute to rational utilization of the limited available time and affect the confidence coefficie
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::406d2c684b8b1cc26cbf432e2aeab8ef
https://doi.org/10.1007/978-3-319-91017-8_27
https://doi.org/10.1007/978-3-319-91017-8_27
Publikováno v:
31st International Symposium on Shock Waves 2 ISBN: 9783319910161
A large-scale free-piston shock tunnel has been built in China Academy of Aerospace Aerodynamics (CAAA). The diameter of the nozzle exit is 2 m and the length is 12.4 m. The large-scale free-piston shock tunnel is called FD-21, which employed three r
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::753d3a3fffef76270dd0e7d597b6d38b
https://doi.org/10.1007/978-3-319-91017-8_26
https://doi.org/10.1007/978-3-319-91017-8_26
Publikováno v:
Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019).
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::cf1e81adb9f4204f99c890ec9035cc22
https://doi.org/10.3850/978-981-11-2730-4_0437-cd
https://doi.org/10.3850/978-981-11-2730-4_0437-cd