Numerical simulation of non-equilibrium reacting flows for supersonic air breathing propulsion applications
FP4 — Training and Mobility of Researchers
- Duration
- 1997-04-01 → 1999-03-31
- EU contribution
- —
- Participants
- 2
- Scheme
- RGI
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Project objective
Between the various advanced technology options that have been proposed in order to develop an efficient launch system into near orbit, air breathing propulsion is probably the nearest term. Specific issues characterizing both diffusive burning and shock assisted combustion engines are related to fuel/air mixing and to chemical kinetics. In particular, finite-rate chemistry effects play a key role in the physics of supersonic combustion and of detonation. The final aim of the research here proposed is to build a numerical tool able to simulate a flow with chemical reactions in non-equilibrium. In this framework, the coupling between turbulence and combustion could be taken into account using probability density function (pdf) models (presumed pdf or Monte-Carlo pdf). Once the appropriate models will have been studied and chosen, they will be implemented in an existing code for 2D geometries (for testing and validating) that will have to be adapted to deal with non-equilibrium effects. Then, 3D flows will be attacked, at first with simple geometries and then with more realistic configurations.
Original text from CORDIS.
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Data: CORDIS, © European Union