推进技术 ›› 2014, Vol. 35 ›› Issue (6): 727-734.

• 气动热力学 总体 • 上一篇    下一篇

前机身/进气道攻角特性的数值与试验研究

陈颖秀1,侯安平1,张 章1,倪奇峰1,脱 伟2,夏爱国2   

  1. 北京航空航天大学 航空发动机气动热力重点实验室,北京 100191;北京航空航天大学 航空发动机气动热力重点实验室,北京 100191;北京航空航天大学 航空发动机气动热力重点实验室,北京 100191;北京航空航天大学 航空发动机气动热力重点实验室,北京 100191;北京航空工程技术研究中心,北京 100076;北京航空工程技术研究中心,北京 100076
  • 发布日期:2021-08-15
  • 作者简介:陈颖秀(1991—),男,硕士生,研究领域为航空发动机气动热力学。E-mail:cyxiu1991@163.com

Numerical and Experimental Studies on Characteristics Under Angle of Attack for Forebody-Inlet

  1. Chinese National Key Laboratory of Aerodynamics & Thermodynamics on Aero-engine,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;Chinese National Key Laboratory of Aerodynamics & Thermodynamics on Aero-engine,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;Chinese National Key Laboratory of Aerodynamics & Thermodynamics on Aero-engine,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;Chinese National Key Laboratory of Aerodynamics & Thermodynamics on Aero-engine,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;Beijing Aeronautical Technology Research Center,Beijing 100076,China;Beijing Aeronautical Technology Research Center,Beijing 100076,China
  • Published:2021-08-15

摘要: 为研究前机身/进气道内外流场的攻角特性,对其一体化模型进行综合求解。将数值计算结果与试验数据进行对比以验证数值方法。分析了不同攻角下前机身对进气道入口气流的影响以及进气道内部流动情况,同时分析了攻角对进气道总压恢复系数和出口总压畸变指数的影响。结果表明:进气道位于机身下侧的布局能在大攻角下降低进气道入口的迎角和马赫数,有效提高飞行极限;在超声来流下,进气道在很宽泛的攻角范围内总压恢复系数都能达到0.94左右,在9°到18°攻角范围内具有较低水平的总压畸变,在此攻角范围之外,总压畸变对攻角的变化很敏感。

关键词: 数值模拟;前机身/进气道;大攻角;总压恢复系数;总压畸变指数

Abstract: In order to study the characteristics of external and internal flow field for forebody-inlet,the united model was simulated. The numerical method has been proved by the comparison between numerical results and the test data. The forebody influence on inlet entrance and internal flow was analyzed at different angles of attack. Furthermore,the angle of attack influence on total pressure recovery coefficient and distortion index was researched. The results show that ventral mounted layout can reduce the angle of attack and Mach number at inlet entrance for high angle of attack,which can improve flight limit. The total pressure recovery coefficient can achieve 0.94 in a broad range of angle of attack under supersonic flow. When angle of attack range is between 9 ° and 18 °,the inlet has a low-level total pressure distortion. However,the total pressure distortion is sensitive to the change of angle of attack when the angle is out of range described above.

Key words: Numerical simulation;Forebody/Inlet;High angle of attack;Total pressure recovery coefficient;Total pressure distortion index