Numerical Simulation of Transient Scramjet Combustion in a Shock Tunnel

Star, Jason B., Edwards, Jack R. Jr., Smart, Michael K. and Baurle, Robert A. (2005). Numerical Simulation of Transient Scramjet Combustion in a Shock Tunnel. In: Proceedings of the 43rd AIAA Aerospace Sciences Meeting and Exhibit. 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, (2005-428-1-2005-428-18). 10-13 January 2005.


Author Star, Jason B.
Edwards, Jack R. Jr.
Smart, Michael K.
Baurle, Robert A.
Title of paper Numerical Simulation of Transient Scramjet Combustion in a Shock Tunnel
Conference name 43rd AIAA Aerospace Sciences Meeting and Exhibit
Conference location Reno, Nevada
Conference dates 10-13 January 2005
Convener American Institute of Aeronautics and Astronautics
Proceedings title Proceedings of the 43rd AIAA Aerospace Sciences Meeting and Exhibit
Place of Publication Reston, Virginia, U.S.A.
Publisher American Institute of Aeronautics and Astronautics
Publication Year 2005
Year available 2005
Sub-type Fully published paper
Start page 2005-428-1
End page 2005-428-18
Total pages 18
Language eng
Abstract/Summary Computational simulations of reactive flow within a hydrogen-fueled scramjet-like geometry experimentally tested in a free piston shock tunnel are presented. The experimental configuration (Odam and Paull, AIAA Paper 2003-5244) involves injection of hydrogen fuel into the scramjet inlet, followed by mixing, shock-induced ignition, and combustion. Experimental results showed significant heat release due to shock induced supersonic combustion. The present steady-state results, performed using a validated threedimensional Navier-Stokes solver, show generally good agreement with experimental data at fuel-off and fuel-on conditions but display a marked sensitivity to the wall temperature boundary condition. This indicates the possible need to account for transient wall heating in simulations of scramjet experiments conducted in short-duration shock-tunnel facilities. The computational results also provide some support for a “radical farming” hypothesis, advanced to explain the ability of the hydrogen-air mixture to auto-ignite at relatively low inlet contraction ratios.
Subjects 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Q-Index Code EX

 
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Created: Tue, 07 Apr 2009, 16:13:39 EST by Mary-Anne Marrington on behalf of School of Mechanical and Mining Engineering