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The main goal of this paper is to analyze the flutter boundary and dynamic load of a supersonic fin. Reduced order mode (ROM) based on Volterra Series is presented to calculate the flutter boundary, and CFD/CSD coupling is used to compute the transient aerodynamic load. The Volterra-based ROM is obtained using the derivative of unsteady aerodynamic step-response, and the infinite plate spline is used...
A simple and efficient mesh deformation method is proposed for time-based nonlinear aeroelastic simulation via CFD/CSD coupling in this paper. With concerned characteristic of multi-structured block, the part of multi-block deformation is studied. A grid deformation technology is developed to fit for the calculation of complex aircraft configuration structure response to nonlinear aeroelastic. The...
This paper presents a method for constructing flow fields with proper orthogonal decomposition (POD) basis functions or modes with great reduction on the computational cost. Using this approach, it is possible to construct the entire aerodynamic flow fields from the knowledge of computed aerodynamic data or measured flow data specified on the aerodynamic surfaces, demonstrating a way to effectively...
The main goal of present paper is to construct an efficient reduced order model (ROM) for unsteady aerodynamic force modeling. Balanced Truncation (BT) is presented to address the problem. For conventional BT method, it is necessary to compute exact controllability and observability grammians. Although it is relatively straightforward to compute these matrices in a control setting where the system...
Computational structural dynamics (CSD) and Computational fluid dynamics (CFD) referring to aeroelasticity are highly nonlinear problems in time domain. Euler equation is solved by finite volume method with dual-time technology to obtain nonlinear unsteady aerodynamic load; the finite element co-rotational theory is applied to model geometric nonlinear structure, and an approximate energy conservation...
The main objective of this paper is to numerically investigate the effects of a divert jet on the overall aerodynamic performance of a generic interceptor missile operating at moderate angle attack. A generic missile interceptor configuration consisting of a long, slender body containing tail fins is simulated in this study. Firstly, K-epsiv, K-omega and S-A turbulent model are evaluated in simulating...
Transonic unsteady aerodynamics model can be obtained by CFD/CSD coupling computation, but it is disadvantaged to analyze and integrate ASE problems because of the high order of model. The high order ASE model is dealt with order reduction technique using system differentiate and analyses and balanced truncation in this paper, and integrate with the low order model. Outlines of this paper can be generalized...
Presented is an investigation into Advection Upstream Splitting Method (AUSM) family schemes. A newly improved version of the AUSM scheme, called AUSMPW+, was developed to increase the accuracy and computational efficiency of AUSM scheme in capturing oblique shock without compromising robustness. With a new definition of the numerical speed of sound at a cell interface, the ability of capturing an...
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