Static/dynamic correction approach for reduced-order modeling of unsteady aerodynamics

被引：0
|
作者：
Thomas, Jeffrey P. [1 ,2 ,3 ]
Dowell, Earl H. [1 ,3 ,4 ]
Hall, Kenneth C. [1 ,2 ,3 ]
机构：
[1] Duke University, Durham, NC 27708-0300, United States
[2] Department of Mechanical Engineering and Materials Science, United States
[3] AIAA, United States
[4] Department of Mechanical Eagineenng and Ma Terials Science, School of Engineering
来源：
Journal of Aircraft | 1600年 / 43卷 / 04期
关键词：
Presented is a newly devised static/dynamic correction approach for eigenvector expansion based reduced-order modeling (ROM). When compared to the fundamental Ritz ROM formulation; along with the static and multiple static correction ROM approaches; the technique is demonstrated to have much better performance in modeling unsteady linearized frequency-domain aerodynamics in region of the complex frequency plane near the imaginary axis; and up to a prescribed frequency of interest. As with the static and multiple static correction approaches; the method requires a directly computed solution at zero frequency. The method then requires one additional direct solution to be computed at some nonzero frequency; which typically is the maximum frequency of interest. When compared to the multiple static corrections method; the method circumvents the necessity of having to determine each of the multiple static corrections; which require a solution to an alternate set of equations that must be formulated and which can be costly to solve for large systems. We also consider the feasibility of using a proper orthogonal decomposition (POD) to determine approximations for the least damped fluid-dynamic eigenvectors. We demonstrate that in certain situations these approximate eigenvectors can be used in conjuction with the static/dynamic correction ROM approach to achieve an improvement in performance over the recently devised POD/ROM method where the POD shapes alone are used as ROM shape vectors. Finally; we illustrate how the method can be coupled with a structural model to compute the Mach-number flutter speed trend for a large computational-fluid-dynamics model of a three-dimensional transonic wing configuration;
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摘要：
Journal article (JA)
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页码：865 / 878
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