|Table of Contents|

Effect of wall surface heat dissipation on performance of supersonic nozzle(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2015年03期
Page:
33-38
Research Field:
研究与设计
Publishing date:

Info

Title:
Effect of wall surface heat dissipation on performance of supersonic nozzle
Author(s):
NAN Xiang-Jun1;  ZHANG Rui2;  ZHANG Liu-huan1
1. Xi’an Aerospace Propulsion Institute, Xi’an 710100, China; 2. Beijing Aerospace Propulsion Institute, Beijing 100076, China
Keywords:
nozzle;  heat dissipation law;  thrust coefficient;  theory analysis
PACS:
V434-34
DOI:
-
Abstract:
One dimensional non-viscous theory is used to calculate the flow characteristics and performance of a divergent nozzle, and analyze the effect of wall surface heat dissipation and heat dissipation law on flowfield, exit dynamic parameters and performance parameters of the nozzle. The calculated results show that the wall surface heat dissipation may cause decrease of static pressure, static temperature and total temperature, but increase of exit Mach number and total pressure, and descend of the nozzle performance, and may result in, with gradual addition of heat dissipation, the nozzle will suffer from under-expansion and over-expansion, but its thrust coefficient becomes gradually decreased. Besides, the law of heat dissipation will have great influence on nozzle performance. The research result indicates when heat dissipating capacity is higher near inlet and lower near from under expansion to critical expansion. The heat dissipation from rear part of the nozzle can achieve a perfect adjusting effect.

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