A pressure-controllable bump based on the pressure-ridge concept
Z Yu, G Huang, C Xia, J Sesterhenn - Aerospace Science and Technology, 2019 - Elsevier
An innovative type of pressure distribution for the hypersonic aircraft forebody (bump) is
presented, and this design is based on the newly established known as pressure ridge (PR) …
presented, and this design is based on the newly established known as pressure ridge (PR) …
Investigation of aerodynamic heating in V-shaped cowl-lip of the inward turning inlet
Z Meng, X Fan, B Xiong, Y Tao - Proceedings of the …, 2019 - journals.sagepub.com
Complex flow field structure, which is induced by the leading edge of V-shaped cowl-lip in
hypersonic inward turning inlet, causes severe thermal load. The V-shaped cowl-lip is …
hypersonic inward turning inlet, causes severe thermal load. The V-shaped cowl-lip is …
[PDF][PDF] 高超声速飞行器一体化方法研究
黄笠舟， 施崇广， 郑晓刚， 李怡庆， 尤延铖 - 航空发动机, 2019 - core.ac.uk
针对高超声速飞行器一体化设计方法现状的分析, 阐明了吸气式发动机与乘波体飞行器之间高效
的一体化对于高超声速飞行的重要作用, 并从理论, 原理, 设计方法3 方面进行介绍 …
的一体化对于高超声速飞行的重要作用, 并从理论, 原理, 设计方法3 方面进行介绍 …
An inverse design method for non-uniform flow inlet with a given shock wave
W Qiao, A Yu, Y Wang - Acta Mathematicae Applicatae Sinica, English …, 2019 - Springer
For the hypersonic inlet and fore-body integrated design, the non-uniform incoming flow
generated by the fore-body will bring a relatively big challenge to the inward-turning inlet …
generated by the fore-body will bring a relatively big challenge to the inward-turning inlet …