亚声速埋入式进气道性能回归分析

推进技术 ›› 2006, Vol. 27 ›› Issue (4): 345-348.

亚声速埋入式进气道性能回归分析

王晓东,袁宁,陈玉春,苏祥荣

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;西北工业大学动力与能源学院;陕西西安710072;空军驻京丰地区军代表室北京100074

发布日期:2021-08-15

Regression analysis on performance of a subsonic submerged inlet

The 31st Research Inst.of CASIC,Beijing 100074,China;The 31st Research Inst.of CASIC,Beijing 100074,China;School of Powerand Energy,Northwestern Polytechnical Univ.,Xi’an 710072,China;AirRegional Representative Office in Fengtai District,Beijing 100074,China

Published:2021-08-15

摘要/Abstract

摘要： 根据某埋入式进气道试验数据建立了计算埋入式亚声速进气道总压恢复系数的经验公式,表现为关于马赫数、流量系数、攻角、侧滑角的函数。该经验公式可用于弹用发动机稳态、起动、加速过程的计算和导弹与发动机一体化设计的数值仿真模型,从而提高发动机性能数值仿真的准确性。

关键词: 埋入式进气道~+;风洞实验;回归分析

Abstract: The relevance functions between total pressure recover coefficient and the parameters(Mach number,angle of attack,flow coefficient,angle of sideslip) for subsonic submerged inlet in turbojet and turbofan engine were investigated.This experiential formula can be used in simulating steady condition,startup,acceleration work process and integrated design of cruise missile and turbofan engine so as to improve the accuracy of 1D engine performance computation.

Key words: Submerged inlet~+;Wind tunnel test;Regression analysis

王晓东,袁宁,陈玉春,苏祥荣. 亚声速埋入式进气道性能回归分析[J]. 推进技术, 2006, 27(4): 345-348.