Computational analysis of flight data on convective heating of the Martian descent vehicle within the framework of the perfect gas model

Cover Page

Cite item

Full Text

Open Access Open Access
Restricted Access Access granted
Restricted Access Subscription or Fee Access

Abstract

The spatial problem of supersonic flow past the MSL descent space vehicle in the dense layers of the Martian atmosphere is solved using the perfect gas model. The system of Reynolds-averaged Navier-Stokes (RANS) equations is numerically integrated together with the Baldwin-Lomax algebraic turbulent mixing model. In addition to studying the flow field patterns in the vicinity of the descent vehicle for real trajectory conditions, the calculated data on convective heating of the surface on the windward and leeward sides are analyzed. Change in the heating conditions during laminar-turbulent transition near the surface is taken into account. A comparison with flight data is presented.

Full Text

Restricted Access

About the authors

S. T. Surzhikov

Ishlinsky Institute for Problems in Mechanics, Russian Academy of Sciences

Author for correspondence.
Email: surg@ipmnet.ru
Russian Federation, Moscow

References

  1. Лунев В.В. Течение реальных газов с большими сверхзвуковыми скоростями. М.: Физматлит. 2007. 760 с.
  2. Землянский Б.А., Лунев В.В., Власов В.И. и др. Конвективный теплообмен летательных аппаратов. М.: Физматлит. 2014. 330 с.
  3. Tannehill J.C., Anderson D.A., Pletcher R.H. Computational Fluid Mechanics and Heat transfer. 1997. Taylor&Francis. 792 p.
  4. Bertin J.J. Hypersonic aerothermodynamics. American Institute of Aeronautics and Astronautics, Inc., Washington, DC. 1994. 608 p.
  5. Суржиков С.Т. Компьютерная аэрофизика спускаемых космических аппаратов. Двухмерные модели. М.: Физматлит, 2018. 543 с.
  6. Hollis B.R., Collier A.S. Turbulent Aeroheating Testing of Mars Science Laboratory Entry Vehicle in Perfect-Gas Nitrogen// AIAA 2007–1208. 2007. 20 p.
  7. Cheatwood F.M., Gnoffo P.A. Users Manual for the Langley Aerothermo-dynamic Upwind Algorithm (LAURA)// NASA TM-4674, April 1996.
  8. Cebeci T., Smith A.N.O. Analysis of Turbulent Boundary Layers. Academic Press. 1974. 404 p.
  9. Baldwin B.S., Lomax H. Thin Layer Approximation and Algebraic Model for Separated Turbulent Flows. AIAA Paper 78–0257. 1978. 8 p.
  10. Суржиков С.Т. Анализ экспериментальных данных по конвективному нагреву модели марсианского спускаемого аппарата с использованием алгебраических моделей турбулентности // Изв. РАН. МЖГ. 2019. № 6. С. 129–140.
  11. Edquist K.T., Hollis B.R., Johnston C.O., Bose D., White T.R., Mahzari M. Mars Science Laboratory Heat Shield Aerothermodynamics: Design and Reconstruction// JSR. 2014. V.51. № v4. P. 1106–1124.
  12. Суржиков С.Т. Радиационно-конвективный нагрев поверхности марсианского спускаемого аппарата MSL при учете турбулентного характера обтекания// Изв. РАН. МЖГ. 2023. № 5. С. 119–137

Supplementary files

Supplementary Files
Action
1. JATS XML
Download
2. Fig. 1. Calculation grid and isotherms in two sections along the x-axis.

Download (1002KB)
Indexing metadata
3. Fig. 2. Longitudinal velocity field Vx = u/V∞ in the vicinity of the MSL SA at t=65.1 s.

Download (748KB)
Indexing metadata
4. Fig. 3. Temperature field in the vicinity of the MSL CA at t=65.1 s.

Download (873KB)
Indexing metadata
5. Fig. 4. Density of convective heat fluxes on the frontal surface of the aerodynamic shield of the MSL spacecraft at t1=61.5 s (a), t2=65.1 s (b), t3=69.3 s (c), t4=74.0 s (d).

Download (829KB)
Indexing metadata
6. Fig. 5. Distributions of convective heat flux densities along the plane of symmetry of the frontal aerodynamic shield of the MSL spacecraft at t1=61.5 s (a), t2=65.1 s (b), t3=69.3 s (c), t4=74.0 s (d). Black curves – laminar flow, colored curves – turbulent flow.

Download (399KB)
Indexing metadata
7. Fig. 6. Distribution of the convective Qw,tot = Qw,hc + Qdif and integral radiative heat flux Qrad densities along the MSL SA surface in the symmetry plane at t = 65 s (left) and t = 74 s (right). Baldwin–Lomax turbulent mixing model. Constant frontal surface temperature Tw = 1000 K. Solid black curve is the total convective heat flux density, dashed line is the heat flux density due to the diffusion flux to the absolutely catalytic surface; dashed line is the heat conductivity component; solid curve with round markers is the integral radiative heat flux density.

Download (340KB)
Indexing metadata

Copyright (c) 2024 Russian Academy of Sciences