前机身/进气道攻角特性的数值与试验研究

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

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

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

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/Abstract

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

陈颖秀,侯安平,张章,倪奇峰,脱伟,夏爱国. 前机身/进气道攻角特性的数值与试验研究[J]. 推进技术, 2014, 35(6): 727-734.

CHEN Ying-xiu¹,HOU An-ping¹,ZHANG Zhang¹,NI Qi-feng¹,TUO Wei²,XIA Ai-guo². Numerical and Experimental Studies on Characteristics Under Angle of Attack for Forebody-Inlet[J]. Journal of Propulsion Technology, 2014, 35(6): 727-734.

参考文献

[1] 刘大响，叶培梁，胡骏，等. 航空燃气涡轮发动机稳定性设计与评定技术 [ M ] . 北京:航空工业出版社， 2004.
[2] 刘振侠，郭东明，张丽芬，等. S形进气道流场数值模拟 [ J ] . 航空动力学报， 2006， 21(6):1064-1068.
[3] 谢文忠，郭荣伟. 双下侧布局二元超声速进气道掺混气动特性 [ J ] . 航空学报， 2007， 28(6):1287-1295.
[4] 李博，梁德旺. 无隔道超声速进气道/前机身一体化计算与试验 [ J ] . 航空学报， 2009， 30(9):1597-1604.
[5] Kevin R Walsh， John G Williams， William G Steenken. Summary of Inlet Characteristics of the F/A-18 High Alpha Research Vehicle [ R ] . AIAA 98-3713.
[6] Podleski S D. Installed F/A-18 Inlet Flow Calculations at 60 deg Angle of Attack and 10 deg Side Slip [ R ] . AIAA 93-1806.
[7] Crawford F Smith. Prediction of Wind Tunnel Effects on the Installed F/A-18 Inlet Flow Field at High Angles-of-Attack [ R ] . NASA Contractor Report 195429， 1995.
[8] Kevin R Walsh， Andrew J Yuhas， John G Williams， et al. Inlet Distortion for an F/A-18A Aircraft During Steady Aerodynamic Conditions up to 60°Angle of Attack [ R ] . NASA Contract NAS 3-26617， 1997.
[9] 郑小清，沈慧俐. 大攻角下前机身-进气道组合体的流场计算 [ J ] . 航空学报， 1990， 11(3): A 161- A 168.
[10] 杨青真，郑勇. 前机身/进气道流场的一体化数值模拟 [ J ] . 计算机仿真， 2006， 23(11):47-49.
[11] 李博. 混压式超音速进气道与弹体一体流场数值计算 [ D ] . 南京:南京航空航天大学， 2001.
[12] 张世英，柏延智. 二元超声速进气道流场数值模拟及分析 [ J ] . 弹箭与制导学报， 2008， 28(3):203-209.
[13] 谢文忠，郭荣伟. 4种布局形式下超声速飞行器进气道气动特性实验对比 [ J ] . 南京航空航天大学学报， 2011， 43(1):13-17.
[14] 朱彦伟，高扬，刘旭东. 双S形进气道流场数值计算与分析 [ J ] . 机械设计与制造， 2010， (4):234-236.
[15] 朱宇，李椿萱，李天. 机体对超音速进气道性能的影响 [ J ] . 飞机设计， 2001， (2):14-17.