COMPUTATIONAL STUDY –THRUST VECTOR CONTROL SUPERSONIC SECONDARY FLOW INJECTION
Author(s):
Ragul B, Anand kumar S, Dinesh kumar M
Keywords:
Abstract
This paper presents the Computational study of flow through the Rocket Nozzle in order to manoeuvre the Rocket by means of Supersonic Secondary Injection of Hot gases. Well-designed nozzles can accelerate these gases to speeds of thousands of meters per second. In addition to accelerating the gases, nozzles are often responsible for steering (or “vectoring”) the flow in order to control the rocket’s direction of flight in supersonic speed.
Article Details
Unique Paper ID: 149088

Publication Volume & Issue: Volume 6, Issue 10

Page(s): 351 - 354
Article Preview & Download


Share This Article

Go To Issue



Call For Paper

Volume 7 Issue 1

Last Date 25 June 2020


About Us

IJIRT.org enables door in research by providing high quality research articles in open access market.

Send us any query related to your research on editor@ijirt.org

Social Media

Google Verified Reviews

Contact Details

Telephone:6351679790
Email: editor@ijirt.org
Website: ijirt.org

Policies