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Injection-gas-composition effects on hypersonic boundary-layer transition

Published online by Cambridge University Press:  10 March 2020

Fernando Miró Miró Open the ORCID record for Fernando Miró Miró [Opens in a new window]  and
Fabio Pinna Open the ORCID record for Fabio Pinna [Opens in a new window]
Fernando Miró Miró*
Affiliation:
Von Kármán Institute for Fluid Dynamics, Rhode-Saint-Genèse1642, Belgium
Fabio Pinna
Affiliation:
Von Kármán Institute for Fluid Dynamics, Rhode-Saint-Genèse1642, Belgium
*
†Email address for correspondence: [email protected]
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Abstract

The thermal protection system in atmospheric-entry and hypersonic-cruise vehicles are oftentimes designed to ablate during their operation, thus injecting a mixture of various gases with distinct properties into the boundary layer. Such outgassing affects the propagation of instabilities within the boundary layer that ultimately originates the transition to turbulence. This work uses linear stability theory, in combination with the e$^{N}$ method, to establish the underlying reason for the experimentally observed advancement/delay of transition in sharp slender hypersonic cones, when injecting lighter/heavier gases. Contrary to the current understanding and experimental correlations, this numerical analysis suggests that such a behaviour is not linked to the isolated effect of the injected gas’ molar weight, but to its combination with the blowing discontinuity, porosity and the appearance of a shocklet, consequence of the injected gas composition. The shocklet constitutes a density gradient that acts on second-mode instabilities like a thermoacoustic impedance.

JFM classification

Boundary Layers: Boundary layer stability Compressible Flows: Compressible boundary layers Instability: Transition to turbulence
Type
JFM Rapids
Information
Journal of Fluid Mechanics , Volume 890 , 10 May 2020 , R4
Copyright
© The Author(s), 2020. Published by Cambridge University Press

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