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
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Last Date 25 February 2020

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