Magnetic Hypersonic Flow Near the Stagnation Point at Low Reynolds Number

Michael Shi-Yuan Chen, Shuxun Chen

ResearchPublished 1968

An investigation of the effects of wall temperature and of a magnetic field on the flow field at the stagnation point of blunt-nosed bodies in low-Reynolds-number hypersonic flow, with the intent of determining the possibility of using small magnetic fields to reduce heat transfer and skin friction in that region. Results indicate that a small magnetic field of the order of 1000 Gauss or less reduces both heat transfer and skin friction in high-altitude flight, but increases shock standoff distance. The strength of magnetic field required is attainable by a permanent magnet. Increasing the wall temperature tends to produce higher values of both the heat-transfer and skin-friction parameters, although the magnitude of the effect is less on the heat-transfer parameter. All of these effects diminish rapidly as the flow approaches the free-molecular-flow limit.

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  • Copyright: RAND Corporation
  • Availability: Available
  • Year: 1968
  • Print Format: Paperback
  • Paperback Pages: 40
  • Paperback Price: $23.00
  • Document Number: RM-5340-PR

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RAND Style Manual
Chen, Michael Shi-Yuan and Shuxun Chen, Magnetic Hypersonic Flow Near the Stagnation Point at Low Reynolds Number, RAND Corporation, RM-5340-PR, 1968. As of September 8, 2024: https://www.rand.org/pubs/research_memoranda/RM5340.html
Chicago Manual of Style
Chen, Michael Shi-Yuan and Shuxun Chen, Magnetic Hypersonic Flow Near the Stagnation Point at Low Reynolds Number. Santa Monica, CA: RAND Corporation, 1968. https://www.rand.org/pubs/research_memoranda/RM5340.html. Also available in print form.
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