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轴对称近似等熵压缩流场的乘波前体优化设计
Optimized design of waverider forebody derived from asymmetric near-isentropic compression flow fields
查看参考文献9篇
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文摘
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以升阻比为优化目标，在来流马赫数Ma＝2～4及飞行高度H＝20km～24km条件下，进行了轴对称近似等熵压缩流场的乘波前体优化设计，通过CFD验证M_∞＝4优化乘波体的气动特性，并研究了Ma＝3优化乘波前体在非设计条件下的气动特性。结果表明：近似等熵压缩下表面的乘波前体在设计条件下具有良好的气流压缩效果，可满足机体／发动机一体化设计的需要；乘波前体升阻比在1.5～1.9之间，纵向压心位置靠后；非设计条件下，压缩波不聚焦，小于设计马赫数升阻比时降低，大于设计马赫数时升阻比略大。 |
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其他语种文摘
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A new kind of waverider forebody with near isentropic lower surface was optimized design. Axsystematic inviscous flow fields of a family of near isentropic surfaces was obtained by solving Euler equation and acted as base flow field , then a family of waverider derived from this base flow field was generated and optimized for maximum L/D at the condition of Ma=2～4 and attitude H = 20km～24km, detailed viscous effects were calculated and included within the optimization progress itself. Shape and aerodynamics of waverider forebody were obtained and CFD results for Mach 4 case was verified. Aerodynamics of Mach 3 waverider at off-design condition was also simulated by CFD. This kind of waverider with high pressure recovery could meet the air-breathing requirement of the vehicle with engine integrated design, but the L/D was smaller than common waverider because of large wave drag. Pressure center was also at the aft of the waverider. Pressure wave did not focus at off-design condition. L/D was increased with Mach number. |
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来源
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推进技术
,2006,27(5):404-409 【核心库】
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关键词
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等熵压缩
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乘波前体＋
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优化设计
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气动特性
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地址
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中国科学院力学研究所, 北京, 100080
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1001-4055 |
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学科
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航空 |
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基金
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国家自然科学基金资助项目
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文献收藏号
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CSCD:2429927
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参考文献 共
9
共1页
|
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1.
O'Niell M K. Optimized scramjet integration on a waverider.
Journal of Aircraft,1992,29(6):1121
|
被引
1
次
|
|
|
|
|
2.
Naruhisa Takashima. Wedge-cone waverider configuration for engine-airframe integration.
Journal of Aircraft,1995,32(5):1144
|
被引
1
次
|
|
|
|
|
3.
Starkey R P. Critical design issues for airbreathing hypersonic waverider missiles.
Journal of Spacecraft and Rockets,2001,38(4):519
|
被引
1
次
|
|
|
|
|
4.
刘嘉. 高超声速飞行器前体压缩性能研究.
应用数学和力学,2004,25(1):85-93
|
被引
3
次
|
|
|
|
|
5.
王发民. 乘波飞行器构型方法研究.
力学学报,2004,36(5):513-518
|
被引
17
次
|
|
|
|
|
6.
Cornors J F. Design criteria for axisymmetric and two-dimensional supersonic inlets and exits.
Design criteria for axisymmetric and two-dimensional supersonic inlets and exits.NACA TN 3589,1956
|
被引
1
次
|
|
|
|
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7.
Corda S. Viscous optimized hypersonic waveriders designed from axisymmetric flow fields.
Viscous optimized hypersonic waveriders designed from axisymmetric flow fields.AIAA 88-0369,1988
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被引
1
次
|
|
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8.
Eckert E R G. Engineering relations for heat transfer and friction in high-velocity laminar and turbulent boundary layer flow over surfaces with constant pressure and temperature.
Transactions of the ASME,1956,78(6):1273-1283
|
被引
18
次
|
|
|
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9.
Nelder J A. A simplex method for function minization.
Computer Journal,1965,7:313
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被引
2
次
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