一种高空高超声速非定常气动力近似模型
AN APPROXIMATE MODEL OF UNSTEADY AERODYNAMICS FOR HYPERSONIC PROBLEMS AT HIGH ALTITUDE
查看参考文献13篇
|
文摘
|
针对高空高马赫数飞行环境和强黏性干扰的物理特性, 在当地流活塞理论的基础上引入有效外形修正, 发展了黏性修正当地流活塞理论, 结合定常N-S方程解给出了高空高马赫数下针对该方法的有效外形的判据, 并通过数值算例对该判据进行了验证.通过对典型尖头薄翼和典型钝头翼的一系列二维非定常算例, 将该方法与一阶活塞理论、基于欧拉(Euler)方程的当地流活塞理论和非定常N-S方程数值解进行了对比. 结果显示在高度为40~70 km、马赫数为10~20范围内, 通过该方法计算得到的非定常气动力与非定常N-S方程数值解吻合较好, 明显优于活塞理论和基于Euler方程的当地流活塞理论.该方法克服了传统的活塞理论和当地流活塞理论不能用于高空高马赫数这类强黏性效应情况的弊端, 在较宽的马赫数、攻角、飞行高度范围内都有良好的适用性, 同时其计算效率远高于非定常N-S方程. |
|
其他语种文摘
|
The paper introduces a local piston theory with viscous correction for the prediction of hypersonic unsteady aerodynamic loads at high altitude where viscous interaction cannot be ignored. A semi-empirical relation for the determination of effective shape for this method at high Mach number and high altitude is presented based on steady Navier-Stokes equations, and validation of the relation is also completed by numerical method. Furthermore, a series of two-dimensional numerical examples with various Mach numbers, angles of attack and operating altitudes for typical thin airfoil and typical blunt airfoil are provided. The unsteady aerodynamic force coefficients are in well agreement with the unsteady Navier-Stokes predictions with altitude in the range of 40 to 70 km and Mach number in the range of 10 to 20. Compared with classical piston theory and local piston theory based on steady Euler equations, this model performs much better at high Mach number and high altitudes when the viscous interaction effects are strong. This model can be applied in supersonic/hypersonic problems with wide range of Mach number, angle of attack and altitude, and has much higher computational efficiency than unsteady Navier-Stokes equations. |
|
来源
|
力学学报
,2013,45(5):690-698 【核心库】
|
|
DOI
|
10.6052/0459-1879-12-382
|
|
关键词
|
高超声速
;
黏性干扰
;
非定常气动力
;
当地流活塞理论
;
黏性修正
|
|
地址
|
中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京, 100190
|
|
语种
|
中文 |
|
文献类型
|
研究性论文 |
|
ISSN
|
0459-1879 |
|
学科
|
航天(宇宙航行) |
|
基金
|
中国科学院LHD青年基金资助项目
;
国家自然科学基金
;
国家自然科学基金近空间重大研究计划
|
|
文献收藏号
|
CSCD:4949642
|
参考文献 共
13
共1页
|
|
1.
McNamara J J.
Aeroelastic and aerothermoelastic analysis of hypersonic vehicles: Current status and future trends. AIAA Paper 2007-2013,2007
|
被引
1
次
|
|
|
|
|
2.
Anderson J D.
Modern Compressible Flow: With Historical Perspective,1990
|
被引
3
次
|
|
|
|
|
3.
Lucia D J. Reduced-order modeling: new approaches for computational physics.
Progress in Aerospace Sciences,2004,40(1/2):51-117
|
被引
43
次
|
|
|
|
|
4.
Morgan H G. Theoretical considerations of flutter at high Mach numbers.
Journal of the Aeronautical Sciences,1958,25(6):371-381
|
被引
4
次
|
|
|
|
|
5.
陈劲松. 超声速和高超声速翼型非定常气动力的一种近似计算方法.
空气动力学学报,1990,8(3):339-343
|
被引
20
次
|
|
|
|
|
6.
张伟伟. 结合定常CFD技术的当地流活塞理论.
西北工业大学学报,2004,22(5):545-549
|
被引
9
次
|
|
|
|
|
7.
张伟伟. 基于当流活塞理论的气动弹性计算方法研究.
力学学报,2005,37(5):632-639
|
被引
22
次
|
|
|
|
|
8.
Zhang W W. Supersonic flutter analysis based on local piston theory.
AIAA Journal,2009,47(10):2321-2328
|
被引
17
次
|
|
|
|
|
9.
McNamara J J. Approximate modeling of unsteady aerodynamics for hypersonic aeroelasticity.
Journal of Aircraft,2010,47(6):1932-1945
|
被引
21
次
|
|
|
|
|
10.
Lighthill M J. Oscillating airfoils at high Mach number.
Journal of the Aeronautical Sciences,1953,20(6):402-406
|
被引
16
次
|
|
|
|
|
11.
Ashley H. Piston theory--A new aerodynamic tool for the aeroelastician.
Journal of the Aeronautical Sciences,1956,23(12):1109-1118
|
被引
47
次
|
|
|
|
|
12.
Anderson J D.
Hypersonic and High Temperature Gas Dynamics,1989
|
被引
46
次
|
|
|
|
|
13.
李维东. 考虑高空粘性干扰效应的乘波体气动性能工程预测方法研究.
宇航学报,2011,32(6):1217-1223
|
被引
7
次
|
|
|
|
|
了解气象卫星更多信息，请访问