带舵旋成体侧向喷流流场特性分析

赵法明; 王江峰

doi:10.13224/j.cnki.jasp.2016.03.025

带舵旋成体侧向喷流流场特性分析

doi: 10.13224/j.cnki.jasp.2016.03.025

南京航空航天大学航空宇航学院, 南京 210016

基金项目:

江苏高校优势学科建设工程项目

详细信息

作者简介:
赵法明(1988-),男,浙江杭州人,博士生,主要从事超/高超声速喷流控制研究.

中图分类号: V211.3
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- 被引次数: 0
出版历程
- 收稿日期: 2014-07-15
- 刊出日期: 2016-03-28

Analysis on flow field characteristics of lateral jet on slender body

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 针对带舵旋成体外形,来流马赫数为2.0,迎角为0°,10°和20°,喷口位于×字舵中间,首先开展了喷主流干扰流场的数值模拟与风洞实验校验,得到相符的喷口附近子午线压力分布,验证了数值模拟方法的可行性;然后根据数值模拟得到的喷主流干扰流场结构和流动参数分布,分析了喷主流干扰流场结构随迎角的变化特点;最后从喷口附近旋成体和尾舵表面压力分布的变化分析了喷主流干扰对气动力/力矩放大因子的影响.研究结果表明:随迎角增大,喷流前激波向喷口靠近,分离区减小,喷主流压比增大,喷流穿透高度增大;气动力/力矩放大因子均大于1.0,随迎角增大,放大因子减小.喷口位于×字舵中间时,喷主流干扰对喷流直接力有增益作用;×字舵的存在减弱了喷流的包裹作用,对流场起到了有利干扰.
- 流场特性 /
- 超声速主流 /
- 侧向喷流 /
- 风洞实验 /
- 放大因子
Abstract: Study was carried out for a slender body with rudders, with free stream Mach number of 2.0, attack angle of 0, 10, 20 degrees respectively, and the jet spout located between the×-shape rudders. First of all, numerical simulation and wind tunnel tests were carried out, and consistent radial pressure distribution near jet spout was obtained, verifying the feasibility of numerical simulation method. And then, the characteristics of change with attack angle of the interaction flow field were analyzed on the basis of flow field structure and flow parameters distribution obtained from numerical simulation. At last, influence of jet interaction on amplification factors was examined according to surface pressure distribution of slender body and rudders near jet spout. Results showed that, with increasing angle of attack, shock before jet moved towards jet spout with reduction of separation region, and pressure ratio increased with augmentation of penetration height. Amplification factors were larger than 1.0 and decreased with increasing angle of attack. When jet spout was located between×-shape rudders, jet interaction was beneficial to the enhancement of jet force. Existence of×-shape rudders eased the wraparound effect of jet, leading to favorable interference to the flow field.
- flow field characteristics /
- supersonic mainstream /
- lateral jet /
- wind tunnel test /
- amplification factor

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参考文献(18)

[1]	戎宜生,刘伟强.再入飞行器鼻锥逆向喷流对流场及气动热的影响[J].航空学报,2010,31(9):1552-1557. RONG Yisheng,LIU Weiqiang.Influence of opposing jet on flow field and aerodynamic heating at nose of reentry vehicle[J].Acta Aeronautica et Astronautica Sinica,2010,31(9):1552-1557.(in Chinese)
[2]	Alkandry H,Boyd I D,Reed E M,et al.Aerodynamic interactions of reaction-control-system jets for atmospheric entry aeroshells[J].AIAA Journal,2013,51(5):1105-1118.
[3]	李波,王一白,杨立军,等.尾部二次喷流抑制喷管分离流动的数值模拟[J].航空动力学报,2013,28(11):2615-2620. LI Bo,WANG Yibai,YANG Lijun,et al.Numerical investigation of nozzle flow separation control by injecting secondary jet from nozzle exit[J].Journal of Aerospace Power,2013,28(11):2615-2620.(in Chinese)
[4]	Schoenenberger M,Rhode M,Paulson J,et al.Characterization of aerodynamic interactions with the Mars Science Laboratory reaction control system using computation and experiment[R].Grapevine,TX:51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition,2013.
[5]	Morimoto N,Yoon J Y,Aso S,et al.Reduction of aerodynamic heating with opposing Jet through extended nozzle in high enthalpy flow[R].AIAA-2014-0705,2014.
[6]	Srivastava B.Asymmetric divert jet performance of a supersonic missile:computational and experimental comparisons[J].Journal of Spacecraft and Rockets,1999,36(5):621-632.
[7]	Graham M J,Weinacht P,Brandeis J.Numerical investigation of supersonic jet interaction for finned bodies[J].Journal of Spacecraft and Rockets,2002,39(3):376-383.
[8]	孙姝,张红英,程克明,等.喷流反压模拟技术在高超声速进气道实验中的应用[J].航空动力学报,2007,22(10):1667-1672. SUN Shu,ZHANG Hongying,CHENG Keming,et al.Back pressure simulation by cavity injection and its application in hypersonic inlet experiment[J].Journal of Aerospace Power,2007,22(10):1667-1672.(in Chinese)
[9]	杨希祥,费阳,江振宇,等.超声速/高超声速来流中侧向喷流干扰流场数值模拟[J].航空动力学报,2010,25(11):2437-2442. YANG Xixiang,FEI Yang,JIANG Zhenyu,et al.Numerical simulation of lateral jet interaction flow field in supersonic/hypersonic flow[J].Journal of Aerospace Power,2010,25(11):2437-2442.(in Chinese)
[10]	陈逖,刘卫东,孙明波,等.超声速湍流边界层中横向声速喷流的混合LES/RANS模拟[J].航空动力学报,2013,28(11):2536-2542. CHEN Ti,LIU Weidong,SUN Mingbo,et al.Hybrid LES/RANS simulation of transverse sonic injection in supersonic turbulent boundary layer[J].Journal of Aerospace Power,2013,28(11):2536-2542.(in Chinese)
[11]	ZHEN Huaping,GAO Zhenxun,LEE Chunhian.Numerical investigation on jet interaction with a compression ramp[J].Chinese Journal of Aeronautics 2013,26(4):898-908.
[12]	Brandeis J,Gill J.Experimental investigation of super-and hypersonic jet interaction on missile configurations[J].Journal of Spacecraft and Rockets,1998,35(3):296-302.
[13]	Graham M J,Weinacht P.Numerical investigation of supersonic jet interaction for axisymmetric bodies[J].Journal of Spacecraft and Rockets,2000,37(5):675-683.
[14]	Dickmann D A,Lu F K.Shock/boundary-layer interaction effects on transverse jets in crossflow over a flat plate[J].Journal of Aircraft,2009,46(6):1132-1141.
[15]	De Spirito J.Factors affecting reaction jet interaction effects on projectiles[R].AIAA-2011-3031,2011.
[16]	Cassel L A.Applying jet interaction technology[J].Journal of Spacecraft and Rockets,2003,40(4):523-537.
[17]	Dickmann D A,Lu F K.Shock/boundary layer interaction effects of transverse jets in cross-flow over a body of revolution[R].AIAA-2009-4146,2009.
[18]	Gnemmi P,Schäfer H.Experimental and numerical investigations of a transverse jet interaction on a missile body[R].AIAA-2005-0052,2005.