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Title: Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles

ORCiD logo [1]; ORCiD logo [2]; ORCiD logo [1]
  1. University of Michigan, 1320 Beal Avenue, Ann Arbor, Michigan 48109, USA
  2. Texas A &, M University, 607‚ÄČA H.R. Bright Bldg., College Station, Texas 77843, USA
Publication Date:
Sponsoring Org.:
OSTI Identifier:
Grant/Contract Number:
Resource Type:
Journal Article: Publisher's Accepted Manuscript
Journal Name:
Journal of Applied Physics
Additional Journal Information:
Journal Volume: 121; Journal Issue: 5; Related Information: CHORUS Timestamp: 2018-02-14 12:32:30; Journal ID: ISSN 0021-8979
American Institute of Physics
Country of Publication:
United States

Citation Formats

Hanquist, Kyle M., Hara, Kentaro, and Boyd, Iain D. Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles. United States: N. p., 2017. Web. doi:10.1063/1.4974961.
Hanquist, Kyle M., Hara, Kentaro, & Boyd, Iain D. Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles. United States. doi:10.1063/1.4974961.
Hanquist, Kyle M., Hara, Kentaro, and Boyd, Iain D. Tue . "Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles". United States. doi:10.1063/1.4974961.
title = {Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles},
author = {Hanquist, Kyle M. and Hara, Kentaro and Boyd, Iain D.},
abstractNote = {},
doi = {10.1063/1.4974961},
journal = {Journal of Applied Physics},
number = 5,
volume = 121,
place = {United States},
year = {Tue Feb 07 00:00:00 EST 2017},
month = {Tue Feb 07 00:00:00 EST 2017}

Journal Article:
Free Publicly Available Full Text
Publisher's Version of Record at 10.1063/1.4974961

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Cited by: 2works
Citation information provided by
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  • The feasibility of cooling hypersonic-vehicle leading-edge structures exposed to severe aerodynamic surface heat fluxes was studied, using a combination of liquid-metal heat pipes and surface-mass-transfer cooling techniques. A generalized, transient, finite-difference-based hypersonic leading-edge cooling model was developed that incorporated these effects and was demonstrated on an assumed aerospace plane-type wing leading edge section and a SCRAMJET engine inlet leading-edge section. The hypersonic leading-edge cooling model was developed using an existing, experimentally verified heat-pipe model. Then the existing heat-pipe model was modified by adding both transpiration and film-cooling options as new surface boundary conditions. The models used to predict the leading-edgemore » surface heat-transfer reduction effects of the transpiration and film cooling were modifications of more-generalized, empirically based models obtained from the literature. It is concluded that cooling leading-edge structures exposed to severe hypersonic-flight environments using a combination of liquid-metal heat pipe, surface transpiration, and film cooling methods appears feasible.« less
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