Calculation of turbulent supersonic jet on modes specific to launch rockets

Аuthors

Kudimov N. F.^1*, Panasenko A. V.^2**, Safronov A. V.^3***, Tretiyakova O. N.^****

1. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
2. Central research institute for special machinery, Zavodskay str., Khotkovo, Moscow region, 141371, Russia
3. Central Research Institute of Machine Building, 4, Pionerskaya st., Korolev, Moscow region, 141070, Russia

*e-mail: itterasai@gmail.com
**e-mail: akpanas@mail.ru
***e-mail: avsafron@tsniimash.ru
****e-mail: tretiyakova_olga@mail.ru

Abstract

The primary goal of the current research was to provide numerical simulation for the analysis turbulent supersonic jets such as isobaric cold, non-isobaric cold and hot jets specific to launch rockets. Also numerical simulation is used to investigate supersonic turbulent hot jet impinging on the wall at angle to the jet centerline axis. In calculating the jet stream at the start of the propulsion and launch rocket the is very important accurate simulation of shock, rarefaction areas, viscous-inviscid interaction in turbulent mixing layer. Numerical simulation based on the three-dimentional Reynolds equations with various turbulent model (Spalart-Allmaras and SST). Spalart-Allmaras model is a one equation model which solves a transport equation for a viscosity-like variable. The SST k- ω turbulence model is a two-equation eddy-viscosity model which has become very popular. The use of a k- ω formulation in the inner parts of the boundary layer makes the model directly usable all the way down to the wall through the viscous sub-layer, hence the SST k- ù model can be used as a Low-Re turbulence model without any extra damping functions. The SST formulation also switches to a k- ω behaviour in the free-stream and thereby avoids the common k- ω problem that the model is too sensitive to the inlet free-stream turbulence properties. For each of the condition studied in this investigation, it was observed that the velocity and pressure along axis provided the satisfactory prediction to the experimental data. Experimental and numerical wall surface pressure distribution satisfactory agreed with each other.

Conclusion

1. The formation and structure of supersonic turbulent jets specific to launch rockets were investigated.
2. Free jet and jet impinging on the wall was investigated.
3. Through the completion of this investigation, the usage of the three-dimentional Reynolds equations with various turbulent model to accurately model turbulent supersonic jets in the wide range has been confirmed. That is the extremely important for land development of gasdynamic of rocket launch.

Keywords:

numerical simulation, the Reynolds equation, turbulence models, the turbulent jet

References

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