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Abstract <p>The work is devoted to the application of the quasi-gasdynamic (QGD) approach to solving problems of flow around manned descent spacecraft on the final section of the trajectory near the Earth’s surface. The main objective of the work is the numerical analysis of the two-dimensional flow around the descent module at different angles of attack. The feature of the calculations performed is the use of the QGD equations and the finite volume method on an irregular triangular grid as a basic model. Parallel computing based on the OpenMP standard is used to speedup calculations. The gas environment is represented by dry atmospheric air. The QGD system is considered in a one-component formulation and is supplemented by the equations of state of an ideal gas and the dependencies of the kinetic coefficients on temperature and pressure. In numerical experiments, the distributions of density, pressure, temperature and velocity modulus are calculated for several angles of attack. The obtained results are consistent with the calculations in the ANSYS CFD package and confirm the effectiveness of the parallel computing technology used.</p>

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Two-Dimensional Calculations of Supersonic Flows around Manned Descent Spacecraft Near the Earth’s Surface

  • 期刊论文

  • 发表日期：

    2025年8月1日

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  • N. I. Tarasov,
  • V. O. Podryga,
  • S. V. Polyakov

摘要

Abstract

The work is devoted to the application of the quasi-gasdynamic (QGD) approach to solving problems of flow around manned descent spacecraft on the final section of the trajectory near the Earth’s surface. The main objective of the work is the numerical analysis of the two-dimensional flow around the descent module at different angles of attack. The feature of the calculations performed is the use of the QGD equations and the finite volume method on an irregular triangular grid as a basic model. Parallel computing based on the OpenMP standard is used to speedup calculations. The gas environment is represented by dry atmospheric air. The QGD system is considered in a one-component formulation and is supplemented by the equations of state of an ideal gas and the dependencies of the kinetic coefficients on temperature and pressure. In numerical experiments, the distributions of density, pressure, temperature and velocity modulus are calculated for several angles of attack. The obtained results are consistent with the calculations in the ANSYS CFD package and confirm the effectiveness of the parallel computing technology used.