Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles

Hanquist, Kyle M.; Hara, Kentaro; Boyd, Iain D.

doi:10.1063/1.4974961

Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles

Journal Article · Wed Feb 01 00:00:00 EST 2017 · Journal of Applied Physics

DOI:https://doi.org/10.1063/1.4974961· OSTI ID:1465324

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Univ. of Michigan, Ann Arbor, MI (United States); THE UNIVERSITY OF MICHIGAN
Texas A & M Univ., College Station, TX (United States)
Univ. of Michigan, Ann Arbor, MI (United States)

Electron transpiration cooling (ETC) is a recently proposed approach to manage the high heating loads experienced at the sharp leading edges of hypersonic vehicles. Computational fluid dynamics (CFD) can be used to investigate the feasibility of ETC in a hypersonic environment. In this paper, a modeling approach is presented for ETC, which includes developing the boundary conditions for electron emission from the surface, accounting for the space-charge limit effects of the near-wall plasma sheath. The space-charge limit models are assessed using 1D direct-kinetic plasma sheath simulations, taking into account the thermionically emitted electrons from the surface. The simulations agree well with the space-charge limit theory proposed by Takamura et al. for emitted electrons with a finite temperature, especially at low values of wall bias, which validates the use of the theoretical model for the hypersonic CFD code. The CFD code with the analytical sheath models is then used for a test case typical of a leading edge radius in a hypersonic flight environment. The CFD results show that ETC can lower the surface temperature of sharp leading edges of hypersonic vehicles, especially at higher velocities, due to the increase in ionized species enabling higher electron heat extraction from the surface. Finally, the CFD results also show that space-charge limit effects can limit the ETC reduction of surface temperatures, in comparison to thermionic emission assuming no effects of the electric field within the sheath.

View Accepted Manuscript (DOE)

Research Organization:: Univ. of Michigan, Ann Arbor, MI (United States)

Sponsoring Organization:: USDOE; USDOE Office of Science (SC), Fusion Energy Sciences (FES) (SC-24)

Grant/Contract Number:: SC0001939

OSTI ID:: 1465324

Alternate ID(s):: OSTI ID: 1361756

Journal Information:: Journal of Applied Physics, Journal Name: Journal of Applied Physics Journal Issue: 5 Vol. 121; ISSN 0021-8979

Publisher:: American Institute of Physics (AIP)Copyright Statement

Country of Publication:: United States

Language:: English

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Cited By (4)

Effect of total emitted electron velocity distribution function on the plasma sheath near a floating wall Qing, Shaowei; Hu, Zhou AIP Advances, Vol. 7, Issue 8 https://doi.org/10.1063/1.5000507	journal	August 2017
Test cases for grid-based direct kinetic modeling of plasma flows Hara, Kentaro; Hanquist, Kyle Plasma Sources Science and Technology, Vol. 27, Issue 6 https://doi.org/10.1088/1361-6595/aac6b9	journal	June 2018
Alternative model of space-charge-limited thermionic current flow through a plasma Campanell, M. D. Physical Review E, Vol. 97, Issue 4 https://doi.org/10.1103/physreve.97.043207	journal	April 2018
Thermionic Cooling of the Target Plasma to a Sub-eV Temperature Campanell, M. D.; Johnson, G. R. Physical Review Letters, Vol. 122, Issue 1 https://doi.org/10.1103/physrevlett.122.015003	journal	January 2019

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Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles

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