Flow modeling of pseudoshocks in backpressured ducts

Smart, Michael K. (2015) Flow modeling of pseudoshocks in backpressured ducts. AIAA Journal, 53 12: 3577-3588. doi:10.2514/1.J054021


Author Smart, Michael K.
Title Flow modeling of pseudoshocks in backpressured ducts
Journal name AIAA Journal   Check publisher's open access policy
ISSN 0001-1452
1533-385X
Publication date 2015-12
Year available 2015
Sub-type Article (original research)
DOI 10.2514/1.J054021
Open Access Status Not yet assessed
Volume 53
Issue 12
Start page 3577
End page 3588
Total pages 12
Place of publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics Inc.
Collection year 2016
Language eng
Formatted abstract
Scramjet operation in the lower hypersonic regime between Mach 4 and 7 is characterized by what is called dual-mode combustion. In this situation, the backpressure generated by heat release in the combustor separates the wall boundary layer upstream of fuel injection, forming a highly complex flow known as a pseudoshock. The pseudoshock phenomenon has been studied extensively in the experimental literature, and its structure has been found to be affected by the duct Mach number, the extent of the wall boundary layer, and the streamwise area distribution of the duct. This paper presents a quasi-one-dimensional analysis technique for calculating the flow through a pseudoshock. It is quite general, and it can be used for ducts with any supersonic inflow, cross-sectional shape, and streamwise area distribution. Comparison of the results of this analysis with experimental data indicates that it provides a good estimate of both the interaction length and the pressure distribution for X-type pseudoshocks that occur in ducts with Mach numbers above two.
Q-Index Code C1
Q-Index Status Provisional Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2016 Collection
 
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