[1]乐贵高,马大为,李自勇.椭圆锥乘波体高超声速流场数值计算[J].南京理工大学学报(自然科学版),2006,(03):257-260.
 LE Gu-i gao,MA Da-we i,LI Z-i yong.Computation of Hypersonic Flowfields for Elliptic-cone-derived Waveriders[J].Journal of Nanjing University of Science and Technology,2006,(03):257-260.
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椭圆锥乘波体高超声速流场数值计算
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《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
期数:
2006年03期
页码:
257-260
栏目:
出版日期:
2006-06-30

文章信息/Info

Title:
Computation of Hypersonic Flowfields for Elliptic-cone-derived Waveriders
作者:
乐贵高1 马大为1 李自勇2
南京理工大学1. 机械工程学院; 2. 动力工程学院, 江苏南京210094
Author(s):
LE Gu-i gao1 MA Da-we i1 LI Z-i yong2
1.School of Mechanical Engineering;2.School of Power Engineering,NUST,Nanjing 210094,China
关键词:
乘波体 高超声速流动 有限差分法
Keywords:
w averiders hyperson ic flow fin ite differencem ethod
分类号:
V 211. 4
摘要:
采用三阶MUSCL型TVD格式,求解可压缩、雷诺平均拉维尔-斯托克斯方程,计算了椭圆锥演化的乘波体高超声速流动问题。在湍流粘性计算中,采用Spalart-A llmaras代数湍流模型,气流马赫数4、攻角为0°、侧滑角分别为0°和10,°雷诺数Re为2×106,通过计算,得到乘波体表面压强、马赫数等参数分布和流动图谱,计算的椭圆锥演化乘波体表面压力系数与实验数据进行了对比,两者有良好的一致性。数值结果表明,在非设计状态下,一定侧滑角引起的乘波体尾部出现局部高压区,文中的计算分析方法对此类乘波体外形的气动设计有一定的参考价值。
Abstract:
In this paper, hypersonic flow s of e lliptic-cone-derived w averiders are simu lated numerica-l ly through the so lut ion of compressible, Reyno lds-averaged Nav ier-Stokes equations using mod if ied MUSCL type TVD scheme. In the computation of the turbulence viscous effects, one-equat ion of Spa-l ar-tA llmaras turbulence mode l is employed. The free flow condit ions forM ach number o f 4 and sideslip ang les from 0 to 10 degrees at zero ang le of attack are considered. The computed pressure coeff-i cients on the waverider surface agree w ith the test data. Numerica l results show that there is a local h igh pressure zone near the waverider base for free flow at a sideslip ang le under the o f-f design cond-i t ion. The computationa lmethod provides reference in aerodynam ic design for such w averider configurations.

参考文献/References:

[ 1] Nonw eiler T B F. Aerodynam ic problem s of m anned space veh ic les [ J]. Journal of the Roya lAeronautica l So ciety, 1959, 63( 4): 521- 528.
[ 2] RasmussenM L. W averider configura tions de rived from inc lined c ircular and elliptic cones [ J]. Journa l o f Spacecraft and Rockets, 1980, 17( 6): 537- 545.
[ 3] JischkeM C, RasmussenM L. Expe rim en tal surface pressures on cone-derived waver iders forM ] = 3- 5 [ J] . Journal o f Spacecraft and Rocke ts, 1983, 20 ( 6): 539- 545.
[ 4] Spalart P, A llmaras S. A one-equation turbulencemode l for aerodynam ic flow s [ A]. 30th Aero space Sc iences M eeting and Exhibit [ C ]. Reno, Nevada, USA: Amer ican Institute o f Aeronautics and A stronautics, 1992. 1- 22.
[ 5] YeeH C. On the imp lementation o f a class of upw ind schem es fo r system o f hyperbolic conservation law s [ R ]. Ca liforn ia: Research Institute fo r Advanced Computer Sc ience, NASA ames Research C enter, 1985. 1- 15.
[ 6] Pulliam T H, Steger J L. Recent improvem ents in eff-i c iency , accuracy, and converg ence for im plicit approx im ate factor iza tion a lgo rithm s [ A ] . 24th A erospace Sc iencesM eeting and Exhib it [ C] . Reno, Nevada, USA: Am er ican Institute o f Aeronautics and Astronau tics, 1985. 1- 37.

备注/Memo

备注/Memo:
作者简介: 乐贵高( 1964- ), 男, 江西崇仁人, 研究员, 博士, 主要研究方向: 飞行器发射/推进技术、计算流体动力 学, E-m ail:Legu igao@ ma il.n just. edu. cn。
更新日期/Last Update: 2006-06-30