亚声S型进气道模型吹风试验特性的研究

推进技术 ›› 2002, Vol. 23 ›› Issue (1): 24-26.

亚声S型进气道模型吹风试验特性的研究

袁宁,刘振德,于守志

航天科工集团公司31所北京100074;航天科工集团公司31所北京100074;航天科工集团公司31所北京100074

发布日期:2021-08-15

Performance investigation by wind tunnel for S-shaped subsonic inlet

The 31st Research Inst.,Beijing 100074,China;The 31st Research Inst.,Beijing 100074,China;The 31st Research Inst.,Beijing 100074,China

Published:2021-08-15

摘要/Abstract

摘要： 采用半经验的方法 ,对某S型进气道的模型试验数据进行了回归 ,建立了弹用涡喷 (扇 )发动机常用S型高亚声速进气道总压恢复系数与飞行马赫数Ma ,流量系数 φ ,攻角α和侧滑角 β的相关函数关系。该半经验公式可用于发动机稳态和启动加速过程一元数值仿真模型 ,从而提高一元发动机性能数值仿真计算的准确性。

关键词: 导弹推进;亚声速进气道;进气道试验;数据分析;回归分析

Abstract: Relevance functions between total pressure recover coefficient and Mach number Ma ,flow coefficient φ ,attack angle α and slip angle β for S sharp inlet of turbine and turbofan engine used by missile in the condition of subsonic was presented. This semi experience formula may be used to simulate steady condition and startuping and acceleration work process. The accuracy of simulating 1D engine performance can be improved by using this formula.

Key words: Missile propulsion;Subsonic inlet;Inlet test;Date analysis;Regression analysis

袁宁,刘振德,于守志. 亚声S型进气道模型吹风试验特性的研究[J]. 推进技术, 2002, 23(1): 24-26.