Abstract
In order to investigate the influence of afterburning on the division flow in the launching process, the simulation method of the gas chemical reaction was applied in the flow field analysis, the computational fluid dynamics numerical method (CFD) was selected. The Standard k-ε turbulence model and the Realizable k-ε turbulence model were used to simulate jet-impingement experiment respectively, the Realizable k-ε turbulence model was validated through comparison with experimental results. The chemical reaction jet flow and the frozen flow were simulated based on the three-dimensional launching pad model. The distributions of temperature, pressure and species were compared on the symmetry plane and in the flow field surrounding deflector. The results show that the afterburning occurs in the jet impingement area and in the mixing layer of air and gas, in these fields the temperature of the chemical reaction jet flow is higher than the frozen flow.
| Translated title of the contribution | Numerical analysis of afterburning's influence on division flow field with deflector |
|---|---|
| Original language | Chinese (Traditional) |
| Pages (from-to) | 393-399 |
| Number of pages | 7 |
| Journal | Guti Huojian Jishu/Journal of Solid Rocket Technology |
| Volume | 43 |
| Issue number | 3 |
| DOIs | |
| Publication status | Published - 1 Jun 2020 |