Supersonic skin-friction drag with tangential wall slot fuel injection and combustion

Kirchhartz, Rainer M., Mee, David J. and Stalker, Raymond J. (2012) Supersonic skin-friction drag with tangential wall slot fuel injection and combustion. AIAA Journal, 50 2: 313-324. doi:10.2514/1.J051073

Author Kirchhartz, Rainer M.
Mee, David J.
Stalker, Raymond J.
Title Supersonic skin-friction drag with tangential wall slot fuel injection and combustion
Journal name AIAA Journal   Check publisher's open access policy
ISSN 0001-1452
Publication date 2012-02
Sub-type Article (original research)
DOI 10.2514/1.J051073
Volume 50
Issue 2
Start page 313
End page 324
Total pages 12
Place of publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics
Collection year 2013
Language eng
Abstract The large viscous drag of hypersonic vehicles is a major obstacle to the successful development of vehicles for prolonged atmospheric travel at high Mach numbers. On such vehicles, this skin-friction drag can be of similar magnitude to that of the inviscid drag on the body. To improve the vehicle’s performance, the net thrust of the propulsion system has to be enhanced, either by increasing the thrust force or by reducing the vehicle drag. Here, reductions in viscous drag can offer a large margin for improvement of the net thrust level. One of the methods for the reduction of supersonic skin friction is the injection of low-density gas into the boundary layer (film cooling). In a recent development, film cooling by slot injection of hydrogen was combined with its combustion within the boundary layer. Analysis and experiments indicated substantial reductions of supersonic skin-friction drag. This paper provides further evidence for substantial skin-friction reductions by presenting shock-tunnel data of direct drag measurements in a circular supersonic combustion chamber with and without pressure gradients and with and without combustion of hydrogen in the boundary layer. The measurements are compared with theories, and the influence of entropy layers and combustor size is investigated. Measurements show a reduction of viscous drag of up to 77%.
Keyword Boundary Layer Combustion
Heat Transfer
Shock Tunnel
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2013 Collection
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Citation counts: TR Web of Science Citation Count  Cited 5 times in Thomson Reuters Web of Science Article | Citations
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Created: Mon, 26 Mar 2012, 12:33:43 EST by System User on behalf of School of Mechanical and Mining Engineering