Semi-empirical relations for pressure distributions in hypersonic regime

Fadgyas, M. C.; Pricop, Mihai Victor; Niculescu, M. L.; Cojocaru, Marius Gabriel; Dumiţrache, Alexandru

doi:10.1063/1.5043975

AIP Conference Proceedings

2018

DOI: 10.1063/1.5043975

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Semi-empirical relations for pressure distributions in hypersonic regime

M. C. Fadgyas

Mihai Victor Pricop

M. L. Niculescu

et al.

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An Engineering Method for Computing the Aerodynamics Performance of Hypersonic Vehicle

Wang

et al. 2020

IOP Conf. Ser.: Mater. Sci. Eng.

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For fast and automatic calculation of aerodynamic in conceptual design of hypersonic vehicles, an aerodynamic fast calculation program based on C/C++ is compiled in this paper. In this paper, the HL-20 lift body and the double radial ball model are selected for the example verification, and the calculation results are compared with the wind tunnel experimental data, it is shown the calculation results is highly consistent with the experiment. The program not only can accurately predict the aerodynamic characteristics of hypersonic vehicles, but also be linked to the optimization program as a C++ library file to realize the shape optimization design.

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An Engineering Method for Computing the Aerodynamics Performance of Hypersonic Vehicle

Wang

et al. 2020

IOP Conf. Ser.: Mater. Sci. Eng.

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Aerothermodynamic Shape Optimization for Re-entry Capsule Using Genetic Algorithms

et al. 2019

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Space hasn’t been for a long time now the final frontier, in the last years more and more spaceships have accessed outer space for different missions, some of them being required to return. The actual and main task of researchers is to find an optimal geometry for new generation of spacecraft which must be reusable and fit the imposed loads (heat flux, pressure, acceleration). The purpose of this paper is to optimize the design of a re-entry capsule configuration, in order to minimize the maximum heat flux on the thermal protection system and to obtain a wanted imposed drag coefficient. For the optimization process we use genetic algorithms and for the solving process, local inclination methods. Even if the latter are low-fidelity methods and do not offer satisfying results on all conditions, we consider them to be good enough for a preliminary study of an optimal design. Thus, this paper purpose is to describe the procedure to obtain an optimal configuration which can be better analyzed with high-fidelity methods.

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Semi-empirical relations for pressure distributions in hypersonic regime

Cited by 2 publications

References 2 publications

An Engineering Method for Computing the Aerodynamics Performance of Hypersonic Vehicle

An Engineering Method for Computing the Aerodynamics Performance of Hypersonic Vehicle

Aerothermodynamic Shape Optimization for Re-entry Capsule Using Genetic Algorithms

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