Paper derives equations governing performance of ramjet using detonative combustion, and evaluates performance; engine layout permits normal detonation wave stabilized in diverging combustion chamber passage, or oblique wave stabilized on wedge; lower speed limit of detonative ramjet and cycle calculation; difficulties encountered by ramjets designed for hypersonic speeds may be alleviated if ramjet is designed to burn incoming air at supersonic velocities in stabilized detonation wave. (see also abstract in SAE -- J v 69 n 11 Nov 1961 p 80-1)
Performance of hypersonic Ramjet using detonative combustion
SAE -- Paper
SAE Meeting ; 1961
1961
8 pages
Conference paper
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Performance of hypersonic ramjet using detonative combustion
Engineering Index Backfile | 1961
|The Performance of a Hypersonic Ramjet Using Detonative Combustion*
SAE Technical Papers | 1961
|Hypersonic Shock-Induced Combustion Ramjet Performance Analysis
British Library Conference Proceedings | 1993
|Investigation of Detonative Combustion Characteristics
British Library Online Contents | 2002
|