Asia-Pacific International Symposium on Aerospace Technology
SEP 13-15, 2010
Xian, PEOPLES R CHINA
The kerosene-fueled scramjet combustor experiments are numerically simulated, for the purpose of code validation and better understanding of flow structure. Full chemically reacting Navier-Stokes equation is numerically solved, and a global reaction mechanism and a reduced 12 species 12 step reaction mechanism are used for kerosene combustion. Computational results using different level of grid refinement and wall boundary conditions are compared with the experimentally measured data. In addition, computed results with different reaction mechanisms are compared. The computed and experimental results agree well. Three dimensional flow structures of different fuel injection scheme are compared. The results show that the subsonic region of the in-cavity fuel injection is located near the sidewall, whereas for the case with upstream single-hole fuel injection, the subsonic region is located near the symmetry plane.
Wan T,Chen LH,Wang J,et al. CFD Simulation of Kerosene-Fueled Supersonic Combustion Ramjet Combustor Experiments[C]PROCEEDINGS OF 2010 ASIA-PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY, VOL 1 AND 2,2010.