Periodic Exhaust Flow through a Converging-Diverging Nozzle Downstream of a Rotating Detonation Engine (AIAA 2014-1015)
52nd, Aerospace sciences meeting; held at the AIAA SciTech Forum 2014 ; 2014 ; National Harbor, MD
2014-01-01
12 pages
Includes bibliographical references and author index
Conference paper
English
© Metadata Copyright the British Library Board and other contributors. All rights reserved.
Numerical simulation of converging-diverging nozzle flow in pulse detonation rocket engine
British Library Online Contents | 2007
|AIAA-2005-1177 STUDY ON DETONATION STRUCTURE PROPAGATING IN A CONVERGING-DIVERGING NOZZLE
British Library Conference Proceedings | 2005
|