高超声速飞行器不只是md才有。。。。。。

来源：百度文库编辑：超级军网时间：2024/04/27 02:06:36

二维带动力吸气式高超声速飞行器绕流的
PNS-NS混合求解
贺旭照1,2 , 乐嘉陵1,2  , 宋文艳1
(1西北工业大学动力与能源学院，710072 西安；
2中国空气动力研究与发展中心计算空气动力研究所，621000 绵阳)

摘要：为了提高吸气式高超声速飞行器绕流的求解效率，采用空间推进求解抛物化PNS(parabolized NavierStokes)方程和时间迭代求解NavierStokes （NS）方程的混合计算流体动力学（CFD）方法来求解高超声速飞行器整机绕流.在超声速占主导的流动区域采用空间推进求解抛物化NS方程的方法，在亚声速和分离区采用时间迭代求解NS方程的方法.对于求解二维带化学反应的吸气式高超声速飞行器绕流，混合CFD方法和完全时间迭代方法相比，可得到同等准确的数值模拟结果，并且求解效率提高了数倍.
关键词：吸气式高超声速飞行器；化学反应流动；抛物化NavierStokes方程；空间推进方法；
混合计算流体动力学方法
中图分类号：V2113    文献标识码：A

PNS-NS combined method for solving two-dimensional
powered airbreathing hypersonic vehicles flowfield
HE Xuzhao1,2，LE Jialing1,2 ，SONG Wenyan1
（1 School of Power and Energy, Northwestern Polytechnical University, Xian 710072, China;
2 Computation Aerodynamics Institute, China Aerodynamic Research and Development Center, Mianyang 621000, China)
Abstract：To improve the computational efficiency of airbreathing hypersonic vehicles flowfield, a combined computational fluid dynamics (CFD) method, which combines space marching method for parabolized NavierStokes (PNS) equations and time iteration method for NavierStokes (NS) equations, was used to simulate airbreathing hypersonic vehicles flowfield. Space marching method was used to solve the PNS equations in the supersonic dominated regions, and time iteration method used to solve the NS equations in the stream direction separation or subsonic dominated regions. For solving the twodimensional（2-D） airbreathing hypersonic vehicles flow field with chemical reaction, the combined CFD procedure can get the same results with the same accuracy and also improve computational efficiency for several folds as compared with traditional time iteration methods.
Key words:airbreathing hypersonic vehicle；chemical reaction flow；
parabolized NavierStokes（PNS）equations；space marching method；
combined computational fluid dynamics (CFD) method二维带动力吸气式高超声速飞行器绕流的
PNS-NS混合求解
贺旭照1,2 , 乐嘉陵1,2  , 宋文艳1
(1西北工业大学动力与能源学院，710072 西安；
2中国空气动力研究与发展中心计算空气动力研究所，621000 绵阳)

摘要：为了提高吸气式高超声速飞行器绕流的求解效率，采用空间推进求解抛物化PNS(parabolized NavierStokes)方程和时间迭代求解NavierStokes （NS）方程的混合计算流体动力学（CFD）方法来求解高超声速飞行器整机绕流.在超声速占主导的流动区域采用空间推进求解抛物化NS方程的方法，在亚声速和分离区采用时间迭代求解NS方程的方法.对于求解二维带化学反应的吸气式高超声速飞行器绕流，混合CFD方法和完全时间迭代方法相比，可得到同等准确的数值模拟结果，并且求解效率提高了数倍.
关键词：吸气式高超声速飞行器；化学反应流动；抛物化NavierStokes方程；空间推进方法；
混合计算流体动力学方法
中图分类号：V2113    文献标识码：A

PNS-NS combined method for solving two-dimensional
powered airbreathing hypersonic vehicles flowfield
HE Xuzhao1,2，LE Jialing1,2 ，SONG Wenyan1
（1 School of Power and Energy, Northwestern Polytechnical University, Xian 710072, China;
2 Computation Aerodynamics Institute, China Aerodynamic Research and Development Center, Mianyang 621000, China)
Abstract：To improve the computational efficiency of airbreathing hypersonic vehicles flowfield, a combined computational fluid dynamics (CFD) method, which combines space marching method for parabolized NavierStokes (PNS) equations and time iteration method for NavierStokes (NS) equations, was used to simulate airbreathing hypersonic vehicles flowfield. Space marching method was used to solve the PNS equations in the supersonic dominated regions, and time iteration method used to solve the NS equations in the stream direction separation or subsonic dominated regions. For solving the twodimensional（2-D） airbreathing hypersonic vehicles flow field with chemical reaction, the combined CFD procedure can get the same results with the same accuracy and also improve computational efficiency for several folds as compared with traditional time iteration methods.
Key words:airbreathing hypersonic vehicle；chemical reaction flow；
parabolized NavierStokes（PNS）equations；space marching method；
combined computational fluid dynamics (CFD) method

强大啊，HKC

楼主是论文党？老发这样的东西。

LZ去哪里找得那么多论文的啊

西北工业大学动力与能源学院，710072 西安；
2中国空气动力研究与发展中心计算空气动力研究所，621000 绵阳)

摘要：为了提高吸气式高超声速飞行器绕流的求解效率，采用空间推进求解抛物化PNS(parabolized NavierStokes)方程和时间迭代求解NavierStokes （NS）方程的混合计算流体动力学（CFD）方法来求解高超声速飞行器整机绕流.在超声速占主导的流动区域采用空间推进求解抛物化NS方程的方法，在亚声速和分离区采用时间迭代求解NS方程的方法.对于求解二维带化学反应的吸气式高超声速飞行器绕流，混合CFD方法和完全时间迭代方法相比，可得到同等准确的数值模拟结果，并且求解效率提高了数倍.
关键词：吸气式高超声速飞行器；化学反应流动；抛物化NavierStokes方程；空间推进方法；
混合计算流体动力学方法
中图分类号：V2113 文献标识码：A

PNS-NS combined method for solving two-dimensional
powered airbreathing hypersonic vehicles flowfield
HE Xuzhao1,2，LE Jialing1,2 ，SONG Wenyan1
（1 School of Power and Energy, Northwestern Polytechnical University, Xian 710072, China;
2 Computation Aerodynamics Institute, China Aerodynamic Research and Development Center, Mianyang 621000, China)
Abstract：To improve the computational efficiency of airbreathing hypersonic vehicles flowfield, a combined computational fluid dynamics (CFD) method, which combines space marching method for parabolized NavierStokes (PNS) equations and time iteration method for NavierStokes (NS) equations, was used to simulate airbreathing hypersonic vehicles flowfield. Space marching method was used to solve the PNS equations in the supersonic dominated regions, and time iteration method used to solve the NS equations in the stream direction separation or subsonic dominated regions. For solving the twodimensional（2-D） airbreathing hypersonic vehicles flow field with chemical reaction, the combined CFD procedure can get the same results with the same accuracy and also improve computational efficiency for several folds as compared with traditional time iteration methods.
Key words:airbreathing hypersonic vehicle；chemical reaction flow；
parabolized NavierStokes（PNS）equations；space marching method；
combined computational fluid dynamics (CFD) method

傻货满天飞发表于 2011-3-4 17:35

平时爱学习、特别是爱搜集

用《中国期刊全文数据库》、维普、万方数据库，搜一下，你这种论文海了去了，别发了。

CF的全体涉密人员内牛满面。。。。。。。

lz今天很high啊

就我自己写的论文而言,偶是不相信论文地!

顶一下。

梅兰竹菊发表于 2011-3-4 18:15

哈哈牛逼

深夜潜行发表于 2011-3-4 19:10

是的，抄完了还不照样毕业，搞不好答辩还得个优秀。但这是真的

ano1225 发表于 2011-3-4 18:21

顶贴捞分

唉，没有暴总气魄啊、

飞行器

提出理论研究与做出实物还有65535光年的距离，而且提出理论还不一定能付诸实践

NASA半壁喷管试验为参考，进行了二维及三维内外流相互作用的数值模拟计算，分析了后体喷管三维流场的特点.从高超声速飞行器机身推进一体化的角度，构建了后体喷管三维构型，进行了不同构型设计对后体喷管性能影响的参数研究.结果表明:后体喷管的三维效应不可忽视，后体喷管侧壁的存在及下壁面长度对性能影响较大.
关键词：高超声速飞行器；一体化设计；后体喷管；三维构型；数值模拟
中图分类号：V235.2 文献标识码：A

Design of three dimensional afterbody/nozzle configuration of airbreathing hypersonic vehicle
XU Dajun, CHEN Bing, CAI Guobiao, XU Xu
(School of Astronautics,Beijing University of Aeronautics and Astronautics, Beijing 100191, China)
Abstract：Three dimensional configuration design of afterbody/nozzle was studied in this paper. Flow filed numerical simulations were conducted on NASA single expansion ramp nozzle experiment model. Numerical simulation results of twodimensional and threedimensional flow field without/with side fence were compared with experiment data and structure of threedimensional flow filed. From the viewpoint of hypersonic vehicle airframe/propulsion integrated design, threedimensional configuration of afterbody/nozzle was constructed with side fences. Parameters of cowl length and side fence inclination angle were investigated to analyze their effects on thrust, lift and pitch moment acted on overall vehicle. The results show three dimensional effect of afterbody/nozzle flow field could not be neglected.
Key words: hypersonic vehicle; integrated design; afterbody/nozzle;
threedimensional configuration; numerical simulation

楼主在发挥TG人多的优势进行人肉

这种论文+摘要的帖子发了好几个了，搞什么飞机？

一片论文加一点摘要就可以YY了？最多只能证明TG在搞研究。要是这容易，到国外期刊上可以检索成千上万类似的论文，都拿回来，岂不是要精尽人亡？

系统内权威刊物就一点价值都没有？照你这么说有什么是可信的？媒体？报纸？ccav？很可信么？满是谣言的网络很可信么？夫妻还有很多同床异梦呢，照你这么说世上还有什么可信的？估计你也就想、就知道看图，告诉你，没有，有也不给你看。最近cd这么多了这么一批说话想问题没层次的。

bigforfex 发表于 2011-3-5 01:41

再教你一句，情报就要善于从真真假假的信息中分析出来，有时候假信息也有用，可以从反面、侧面推论。否则你告诉大家，哪一类信息是绝对可靠的？哦，有的，tg国防部官方正式信息是么？那也有烟雾弹，比如关友飞忽悠md的话，能信么？还是有图就可信？要不你自己做军中高官去吧，你整天可以看到内部密级文件了。

论文党的始祖是那个贴整体式座舱盖的火星人，那个打脸帖，很火，原来兰州也跑步进入新时代！

高超声速飞行器不只是md才有。。。。。。高大上的高超声速飞行器原来是鸡肋？高大上的高超声速飞行器原来是鸡肋？所谓“高超声速”的飞行器，不一定是超过5马赫高超声速飞行器不需要翅膀？日本高超声速飞行器近期研究重点印度开展高超声速飞行器风洞试验印开展高超声速飞行器风洞试验美国高超声速飞行器发展路线图中国空军空天一体重点打造高超声速飞行器中国空军空天一体重点打造高超声速飞行器中国空军空天一体重点打造高超声速飞行器