Aerothermodynamic comparison of two- and three-dimensional rarefied hypersonic cavity flows

Rodrigo Cassineli Palharini, Thomas Scanlon, Jason Reese

Research output: Contribution to journalArticle

8 Citations (Scopus)

Abstract

The thermal protection system is a key element in atmospheric re-entry missions of aerospace vehicles. Usually, in the thermal load calculations, the analysis assumes that the vehicle has a smooth surface. However, discontinuities or imperfections are often present on the aerospace vehicle surfaces due to fabrication tolerances, sensor installations, spaces between the thermal protection plates, and differential expansion or ablation rates between non-similar materials. In the present work, rarefied hypersonic flows over two- and three-dimensional cavities at an altitude of 80km in the Earth’s atmosphere are studied numerically. To model flows in the transitional regime, where the validity of the Navier Stokes equations is questionable, the direct simulation Monte Carlo method has been used. The primary goal is to assess the sensitivity of heat transfer, pressure, and skin-friction coefficients for a family of two- and three-dimensional cavities defined by different length-to-depth ratios. The analysis shows that an assumption of two-dimensionality plays a key role in the over prediction of the aerodynamic properties. Previous work using a continuum approach shows that two recirculation regions and flow attachment occurs when the length-to-depth ratio is equal to 14; however, the same phenomena are observed in the transitional regime when the cavity length-to-depth ratio is equal to 4. A study of the influence of the cavity width has also been conducted. It is shown that increasing the cavity width results in an augmentation of the surface aerothermodynamic quantities
LanguageEnglish
Pages1619-1630
Number of pages12
JournalJournal of Spacecraft and Rockets
Volume51
Issue number5
Early online date11 Jun 2014
DOIs
Publication statusPublished - Sep 2014
Event43rd AIAA Thermophysics Conference - LA, New Orleans, United States
Duration: 25 Jun 201228 Jun 2012

Fingerprint

aerothermodynamics
cavity flow
hypersonics
Hypersonic aerodynamics
Aerospace vehicles
cavity
cavities
aerospace vehicles
thermal protection
Hypersonic flow
Earth atmosphere
Skin friction
Reentry
Thermal load
Ablation
Navier Stokes equations
Aerodynamics
Monte Carlo methods
hypersonic flow
reentry

Keywords

  • aerothermodynamics
  • rarefied hypersonic flows
  • Monte Carlo method
  • cavities

Cite this

Cassineli Palharini, Rodrigo ; Scanlon, Thomas ; Reese, Jason. / Aerothermodynamic comparison of two- and three-dimensional rarefied hypersonic cavity flows. In: Journal of Spacecraft and Rockets. 2014 ; Vol. 51, No. 5. pp. 1619-1630.
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Aerothermodynamic comparison of two- and three-dimensional rarefied hypersonic cavity flows. / Cassineli Palharini, Rodrigo; Scanlon, Thomas; Reese, Jason.

In: Journal of Spacecraft and Rockets, Vol. 51, No. 5, 09.2014, p. 1619-1630.

Research output: Contribution to journalArticle

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