Computational Simulation of Conjugated Problem of External Aerodynamics and Internal Heat and Mass Transfer in High-Speed Aircraft Composite Construct

Dimitrienko, Yu. I.; Koryakov, Mikhail; Zakharov, A. A.

doi:10.18178/ijmerr.6.1.58-64

Cited by 10 publications

(2 citation statements)

References 3 publications

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“…In recent years, a large number of flight tests have been carried out for hypersonic boundary transition and shock-border layer interference [4][5] . Such as the Hypersonic International Flight Research Experimentation (HIFiRE ) program jointly implemented by the Air Force Research Laboratory (AFRL) of the United States and Australian Defence Science and Technology Group (DSTG), with a total of 3 flight tests dedicated to related issues (HIFiRE-1, 5, 9).…”

Section: Introductionmentioning

confidence: 99%

Low-Cost and Aerodynamics-Aim Hypersonic Flight Experiment MF-1

Xiao

et al. 2020

MATEC Web Conf.

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For increasing understanding of fundamental hypersonic phenomena, the flight test program, named MF-1, is to gather fundamental scientific and engineering data on the physics and technologies critical to future operational hypersonic flight with low-cost flight test platform, which is built on the retrofitted rockets. The MF-1 program is a hypersonic flight test program executed by China Aerodynamic Research and Development Center (CARDC). The MF-1 flight flew in December 2015. The flight focuses primarily on integration of instrumentation on the test vehicle, with application to boundary layer transition and shock interaction experiments. The MF-1 payload consists of a blunted 7°half angle cone, a cylinder and 33° flare configuration. The payload was boosted to Mach 5.32 utilizing a solid-rocket booster without control for the whole flight. The flight was fully successful, and measured transition under supersonic and hypersonic conditions. The heat flux data were given by the three-dimensional thermal identification method to discriminate transition zone. The preliminary analysis shows that the real-time flight data obtained by MF-1 are reliable and can be used to validate the transition predicting model and software. The results show that the existing model is able to predict the transition location of cone at a small angle-of-attack for supersonic or hypersonic flow. This paper describes the MF-1 mission and some general conclusions derived from the experiment.

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Section: Introductionmentioning

confidence: 99%

Low-Cost and Aerodynamics-Aim Hypersonic Flight Experiment MF-1

Xiao

et al. 2020

MATEC Web Conf.

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“…Software package SIGMA has been successfully applied for numerical solutions of a wide range of problems in aerospace engineering for over ten years (e.g. see [14,15]). It is developed by Computational Mathematics and Mathematical Physics Department of Bauman Moscow State Technical University.…”

Section: Introductionmentioning

confidence: 99%

Development of Preprocessor of SIGMA Software for Computer Simulation in Aerospace Engineering

Dimitrienko¹,

Zakharov²

2018

Proceedings of the International Conference "Actual Issues of Mechanical Engineering" (AIME 2018)

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The paper covers the area of block-structured adaptive grid generation for finite difference, finite element and finite volume methods. It deals with a problem of development of information technologies and algorithms for generating such grids in complex geometries. Its key idea is to bring together the different existing techniques for computer-aided geometric design of domains, grid generation, grid concentration and grid subdivision. The methods used for a construction of domain geometries, working with block-structured quasi-continuous grids, a subdivision of block-structured adaptive grids into vertex-centered control volumes, generation of ghost nodes and cells, calculation of distances to boundaries are discussed. It is described of the software interfaces of the geometry editor and the mesh generator that were developed in the SIGMA preprocessor. The results of the generation of three-dimensional adaptive grids for the domain of external flow near a hemisphere, flow around a surface of the high-speed aircraft of Falcon HTV-2 type and for the domain of the gap between a wheel and a body of an aircraft are analyzed. The presented methods and algorithms for grid generation have the following advantages: 1. The grids are structured and mesh cells are hexahedra in the entire complex curvilinear computational domain. 2. The grids can be applied for finite difference methods. 3. The grid lines are adjusting with the flow in the whole domain. Keywords-block-structured adaptive grid, finite difference grid, computer-aided geometric design, complex domain, mesh subdivision, preprocessing

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