Based on premise that supersonic burning is possible, performance of ramjet cycles is calculated over range of flight Mach numbers from 4 to 7; effects of parameters such an inlet design, combustor area, divergence, wall friction, and nozzle performance; estimates of engine weight and cooling loads included.
Analysis of ramjet engines using supersonic combustion
NACA -- Tech Note
NACA -- Technical Note ; n 4386
1958
49 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
An analysis of ramjet engines using supersonic combustion
TIBKAT | 1958
|Supersonic Combustion Ramjet Research
NTIS | 2012
|