一种乘波前体进气道的一体化设计及性能分析

贺旭照; 秦思; 周正; 倪鸿礼

一种乘波前体进气道的一体化设计及性能分析

贺旭照^1,2,
秦思²,
周正²,
倪鸿礼^1,2

1.
中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室, 四川绵阳 621000
2.
中国空气动力研究与发展中心吸气式高超声速技术研究中心, 四川绵阳 621000

基金项目: 国家自然科学基金(90916012,91216303)

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出版历程
- 收稿日期: 2012-03-11
- 刊出日期: 2013-06-28

Integrated design and performance analysis of waveriderforebody and inlet

1.
Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
2.
Air-breathing Hypersonic Technology Research Center, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 采用特征线方法设计了具有直线初始激波、内收缩段消除激波反射、出口参数均匀可控的基准内锥流场.基于密切内锥(osculating inward turning cone,OIC)乘波体设计方法,发展了一体化密切内锥乘波前体进气道(osculating inward turning cone waverider inlet,OICWI)设计技术.基于一体化基准内锥流场和前体进气道设计技术,设计了密切内锥乘波前体进气道.采用数值软件对设计的乘波前体进气道进行了仿真分析,结论如下:①OICWI的设计是遵循气动原理的.②一体化密切内锥乘波前体进气道的前缘形状、内收缩比及出口参数可以根据需求定量准确设计.③理论设计结果和模拟结果吻合一致,证明设计方法是正确可靠的.④数值模拟研究结果表明一体化密切内锥乘波前体进气道具有较好的出口流场均匀度及较高的流量捕获率和较高的总压恢复特性.
- 乘波前体 /
- 超声速进气道 /
- 一体化设计 /
- 密切内锥 /
- 流线追踪
Abstract: The basic inward turning cone was designed by methods of characteristics which were represented by straight initial shock wave and inner compression section shock wave cancelation, controllable flow parameters and uniformity exit inner compression section. The integrated osculating inward turning cone waverider inlet(OICWI) design methods were developed based on the osculating inward turning cone (OIC) waverider design methods. Based on the designed basic inward turning cone flow field and OICWI design methods, an OICWI was designed. The OICW's performances were analyzed by numerical ways. The results show that:(1)The integrated waverider inlet design methods agree well with aerodynamic principles. (2)The waverider-inlet's shape can be easily controlled by adjusting inlet capture curve, front capture curve and basic flow field structure. (3)Numerical simulation results agree well with the design results and the flow field structures are consistent with each other, showing that the integrated design methods are correct. (4)The viscous results on design and off-design conditions show that OICWI has high pressure recovery and flow capture characteristics, and the flow field parameters are uniform in the inlet exit plane.
- waverider forebody /
- supersonic inlet /
- integrated design /
- osculating inward turning cone /
- streamline tracing

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参考文献(16)

[1]	Haney J W,Beaulieu W D.Wave rider inlet integration issues[R].AIAA 1994-0383,1994.
[2]	Kashif H J,Varnavas C S.Airframe-propulsion integration methodology for waverider-derived hypersonic cruise aircraft design concepts[R].AIAA 2004-1201,2004.
[3]	Eggers T,Novelli P.Design studies for a Mach 8 dual mode ramjet flight test vehicle[R].AlAA 99-4877,1999.
[4]	Walker S,Tang Ming,Morris S.Falcon HTV-3X:a reusable hypersonic test bed[R].AIAA-2008-2544,2008.
[5]	Joseph M H,James S M,Richard C M.The X-51A scramjet engine flight demonstration program[R].AIAA 2008-2540,2008.
[6]	Joseph M H,James S M,Richard C M,et al.The X-51A scramjet engine flight demonstration program[R].AIAA 2008-2540,2008.
[7]	Matthew P B,Steven P S,Thomas J J,et al.Effect of freestream noise on roughness-induced transition for the X-51A Forebody[R].AIAA 2008-0592,2008.
[8]	Richard M, Scott M.X-51 development:a chiefengineer's perspective[R].AIAA 2011-2237,2011.
[9]	Anderson B H.Design of supersonic inlets by a computer program incorporating the method of characteristics[R].NASA TN D-4960,1969.
[10]	Sannu M.Internal axisymmetric conical flow[R].AIAA Journal,1967,5(7):1043-1047.
[11]	贺旭照,倪鸿礼.密切内锥乘波体设计方法和性能分析[J].力学学报,2011,43(5):896-902. HE Xuzhao NI Hongli.Osculating inward turning cone-design methods and performance analysis[J].Acta Sinica,2011,43(5):896-902.(in Chinese)
[12]	贺旭照,倪鸿礼.密切曲面锥乘波体设计方法和性能分析[J].力学学报,2011,43(6):1077-1082. HE Xuzhao,NI Hongli.Osculating curved cone(OCC) waverider-design methods and performance analysis[J].Acta Sinica,2011,43(6):1077-1082.(in Chinese)
[13]	贺旭照,周正,倪鸿礼.密切内锥乘波前体进气道一体化设计和性能分析[J].推进技术,2012,33(4):510-515. HE Xuzhao,ZHOU Zheng,NI Hongli.Integrated design methods and performance analyses of osculating inward turning cone waverider forebody inlet[J].Journal of Propulsion Technology,2012,33(4):510-515.(in Chinese)
[14]	贺旭照,赵慧勇,乐嘉陵.考虑可压缩与热传导的壁面函数边界条件及其应用[J].空气动力学报,2006,24(4):478-482. HE Xuzhao,ZHAO Huiyong,LE Jialing.Application of wall function boundary condition considering heat transfer and compressibility[J].Acta Aerodynamic Sinica,2006,24(4):478-482.(in Chinese)
[15]	贺旭照,乐嘉陵,宋文艳.二维带动力吸气式高超声速飞行器扰流的PNS-NS混合求解[J].航空动力学报,2009,24(12):563-570. HE Xuzhao,LE Jialing,SONG Wenyan.PNS-NS combined method for solving two-dimensional powered airbreathing hypersonic vehicles flowfield[J].Journal of Aerospace Power,2009,24(12):563-570.(in Chinese)
[16]	贺旭照,乐嘉陵,宋文燕,等.基于轴对称喷管的三维内收缩进气道的设计与初步评估[J].推进技术,2010,31(2):438-443. HE Xuzhao,LEJialing,SONG Wenyan,et al.3D inward turning inlet design basing on axisymmetric nozzle and its prelim inary assessment[J].Journal of Propulsion Technology,2010,31(2):438-443.(in Chinese)