Nonequilibrium hydrogen combustion in one- and two-phase supersonic flow
- National Central Univ., Chung Li (Taiwan, Province of China). Dept. of Mechanical Engineering
- Academia Sinica, Taipei (Taiwan, Province of China). Inst. of Physics
A time-splitting method for the numerical simulation of stiff nonequilibrium combustion problem was developed. The algorithm has been applied to simulate the shock-induced combustion and to investigate a supersonic one-and two-phase flowfield. The results are physically reasonable and demonstrate that the presence of particles has a dramatic effect on the nozzle flowfield and the thrust. Supersonic combustion usually happens in high speed flying aerodynamic problems, such as supersonic combustion ramjet (scramjet) engine for hypersonic airbreathing vehicles. Particularly for the scramjet engine, due to short residence time in the combustion chamber, it still contains incomplete combustion fuel as it enters the nozzle. For solid propellant rocket motors, the exhaust stream contains particles of aluminum oxide. In these two-phase nozzle flows, transfer of momentum and heat between gas particles often result in a decrease of nozzle efficiency.
- OSTI ID:
- 483831
- Journal Information:
- International Communications in Heat and Mass Transfer, Vol. 24, Issue 3; Other Information: PBD: May-Jun 1997
- Country of Publication:
- United States
- Language:
- English
Similar Records
International Symposium on Air Breathing Engines, 10th, Nottingham, England, Sept. 1-6, 1991, Proceedings. Vols. 1 2
Ascent performance feasibility of the national aerospace plane