Methods for the Accurate Computations of Hypersonic Flows

Kim, Kyu Hong; Kim, Chongam; Rho, Oh-Hyun

doi:10.1006/jcph.2001.6873

Cited by 477 publications

(154 citation statements)

References 16 publications

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“…Depending on how to linearize the convective term of Eq. (6), Roe's FDS (Flux Difference Splitting) [18], modified Roe's FDS [19], AUSM, and AUSMPW+ [20] are implemented. Mathematical details of each method are found in reference papers, and can be omitted here.…”

Section: Edison_cfdmentioning

confidence: 99%

Development of an Engineering Education Framework for Aerodynamic Shape Optimization

Kwon¹,

Lee²,

Ryu³

et al. 2013

International Journal of Aeronautical and Space Sciences

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Design optimization is a mathematical process to find an optimal solution through the use of formal optimization algorithms. Design plays a vital role in the engineering field; therefore, using design tools in education and research is becoming more and more important. Recently, numerical design optimization in fluid mechanics, which uses computational fluid dynamics (CFD), has numerous applications in the engineering field, because of the rapid development of high-performance computing resources. However, it is difficult to find design optimization software and contents for educational purposes in aerospace engineering. In the present study, we have developed an aerodynamic design framework specifically for an airfoil, based on the EDucation-research Integration through Simulation On the Net (EDISON) portal. The airfoil design framework is composed of three subparts: a geometry kernel, CFD flow analysis, and an optimization algorithm. Through a seamless interface among the subparts, an iterative design process is conducted. In addition, the CFD flow analysis and the design framework are provided through a web-based portal system, while the computation is taken care of by a supercomputing facility. In addition to the software development, educational contents are developed for lectures associated with design optimization in aerospace and mechanical engineering education programs. The software and content developed in this study is expected to be used as a tool for e-learning material, for education and research in universities.

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Section: Edison_cfdmentioning

confidence: 99%

Development of an Engineering Education Framework for Aerodynamic Shape Optimization

Kwon¹,

Lee²,

Ryu³

et al. 2013

International Journal of Aeronautical and Space Sciences

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show abstract

“…As a spatial flux scheme, AUSMPW+ [14] is used to remove oscillations of AUSM+ near wall where a strong shock passes by, while maintaining the accuracy of the original scheme. A second-order MUSCL [15] and LU-SGS [16](Lower-Upper Symmetric Gauss-Seidel) time integration method is adopted in this solver, and a dual time stepping method is employed for an unsteady simulation.…”

Section: Govern Ing Equationmentioning

confidence: 99%

Effects of Angles of Attack and Throttling Conditions on Supersonic Inlet Buzz

Namkoung¹,

Hong²,

Kim³

et al. 2012

International Journal of Aeronautical and Space Sciences

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A series of numerical simulations are carried out to analyze a supersonic inlet buzz, which is an unsteady pressure oscillation phenomenon around a supersonic inlet. A simple but efficient geometry, experimentally adopted by Nagashima, is chosen for the analysis of unsteady flow physics. Among the two sets of simulations considered in this study, the effects of various throttling conditions are firstly examined. It is seen that the major physical characteristic of the inlet buzz can be obtained by inviscid computations only and the computed flow patterns inside and around the inlet are qualitatively consistent with the experimental observations. The dominant frequency of the inlet buzz increases as throttle area decreases, and the computed frequency is approximately 60Hz or 15% lower than the experimental data, but interestingly, this gap is constant for all the test cases and shock structures are similar. Secondly, inviscid calculations are performed to examine the effect regarding angle of attack. It is found that patterns of pressure oscillation histories and distortion due to asymmetric (or three-dimensional) shock structures are substantially affected by angle of attack. The dominant frequency of the inlet buzz, however, does not change noticeably even in regards to a wide range of angle of attacks.Key words: supersonic inlet buzz, effect of angle of attack, asymmetric shock structure, distortion This is an Open Access article distributed under the terms of the Creative Commons Attribution Non-Commercial License (http://creativecommons.org/licenses/bync/3.0/) which permits unrestricted non-commercial use, distribution, and reproduction in any medium, provided the original work is properly cited.

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“…In the supersonic regime with discontinuities such as shock waves, however, the scheme becomes numerically unstable. To avoid such non-physical oscillation, the concept of total variation diminishing (TVD) and the AUSMPW+ scheme were used for the inviscid flux calculation, as the upwind schemes [10].…”

Section: Introductionmentioning

confidence: 99%

On the Assessment of Compressibility Effects of Two-Equation Turbulence Models for Supersonic Transition Flow with Flow Separation

Sung¹,

Kim²,

Yeom³

et al. 2013

International Journal of Aeronautical and Space Sciences

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An assessment of two-equation turbulence models, the low Reynolds k-ε and k-ω SST models, with the compressibility corrections proposed by Sarkar and Wilcox, has been performed. The compressibility models are evaluated by investigating transonic or supersonic flows, including the arc-bump, transonic diffuser, supersonic jet impingement, and unsteady supersonic diffuser. A unified implicit finite volume scheme, consisting of mass, momentum, and energy conservation equations, is used, and the results are compared with experimental data. The model accuracy is found to depend strongly on the flow separation behavior. An MPI (Message Passing Interface) parallel computing scheme is implemented.

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Methods for the Accurate Computations of Hypersonic Flows

Cited by 477 publications

References 16 publications

Development of an Engineering Education Framework for Aerodynamic Shape Optimization

Development of an Engineering Education Framework for Aerodynamic Shape Optimization

Effects of Angles of Attack and Throttling Conditions on Supersonic Inlet Buzz

On the Assessment of Compressibility Effects of Two-Equation Turbulence Models for Supersonic Transition Flow with Flow Separation

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