Control of hypersonic turbulent skin friction by boundary-layer combustion of hydrogen

Stalker, R.J. (2005) Control of hypersonic turbulent skin friction by boundary-layer combustion of hydrogen. Journal of Spacecraft And Rockets, 42 4: 577-587. doi:10.2514/1.8699

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Author Stalker, R.J.
Title Control of hypersonic turbulent skin friction by boundary-layer combustion of hydrogen
Journal name Journal of Spacecraft And Rockets   Check publisher's open access policy
ISSN 0022-4650
Publication date 2005
Sub-type Article (original research)
DOI 10.2514/1.8699
Open Access Status File (Author Post-print)
Volume 42
Issue 4
Start page 577
End page 587
Total pages 11
Editor R. Kimmel
Place of publication RESTON, VA, USA
Publisher American Institute of Aeronautics and Astronautics
Collection year 2005
Language eng
Subject C1
290200 Aerospace Engineering
690302 Space transport
Abstract Shvab-Zeldovich coupling of flow variables has been used to extend Van Driest's theory of turbulent boundary-layer skin friction to include injection and combustion of hydrogen in the boundary layer. The resulting theory is used to make predictions of skin friction and heat transfer that are found to be consistent with experimental and numerical results. Using the theory to extrapolate to larger downstream distances at the same experimental conditions, it is found that the reduction in skin-friction drag with hydrogen mixing and combustion is three times that with mixing alone. In application to flow on a flat plate at mainstream velocities of 2, 4, and 6 knits, and Reynolds numbers from 3 X 10(6) to 1 x 10(8), injection and combustion of hydrogen yielded values of skin-friction drag that were less than one-half of the no-injection skin-friction drag, together with a net reduction in heat transfer when the combustion heat release in air was less than the stagnation enthalpy. The mass efficiency of hydrogen injection, as measured by effective specific impulse values, was approximately 2000 s.
Keyword Engineering, Aerospace
Heat Transfer
Flat Plates
Q-Index Code C1
Q-Index Status Provisional Code
Institutional Status UQ

 
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Created: Wed, 15 Aug 2007, 06:54:57 EST