Techno Press
You logged in as Techno Press

Advances in Aircraft and Spacecraft Science
  Volume 2, Number 2, April 2015 , pages 183-198
DOI: https://doi.org/10.12989/aas.2015.2.2.183
 

Thrust augmentation through after-burning in scramjet nozzles
Michael J. Candon, Hideaki Ogawa and Graham E. Dorrington

 
Abstract
    Scramjets are a class of hypersonic airbreathing engine that are associated with realizing the technology required for economical, reliable access-to-space and high-speed atmospheric transport. Afterburning augments the thrust produced by the scramjet nozzle and creates a more robust nozzle design. This paper presents a numerical study of three parameters and the effect that they have on thrust augmentation. These parameters include the injection pressure, injection angle and streamwise injection position. It is shown that significant levels of thrust augmentation are produced based upon contributions from increased pressure, mass flow and energy in the nozzle. Further understanding of the phenomenon by which thrust augmentation is being produced is provided in the form of a force contribution breakdown, analysis of the nozzle flowfields and finally the analysis of the surface pressure and shear stress distributions acting upon the nozzle wall.
 
Key Words
    after-burning; combustion; CFD; hypersonic flow; nozzle; scramjet
 
Address
Michael J. Candon, Hideaki Ogawa and Graham E. Dorrington: School of Aerospace, Mechanical and Manufacturing Engineering, RMIT University, GPO Box 2476, Melbourne, VIC 3001, Australia
 

Techno-Press: Publishers of international journals and conference proceedings.       Copyright © 2024 Techno Press
P.O. Box 33, Yuseong, Daejeon 305-600 Korea, Tel: +82-42-828-7996, Fax : +82-42-828-7997, Email: info@techno-press.com