Abstract
One of the possible flow schemes within the channel of a supersonic axisymmetric entrance diffuser is considered. The channel is formed by the surfaces of the central body of the diffuser and its outer surface and has an annular section. Axisymmetric flow in the channel of such a diffuser is calculated in the presence of an oblique shock in front of the separation region formed at the corner of the central body.
Full Text 
Sign-in/Register to access full text options
Sign-in/Register to access full text options 
Paper version not known
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
