Launch vehicle base heating prediction due to reversed flow and nozzle wall ablation
- Funding Agency: Indian Space Research Organisation
- Project Summary: The interaction of under-expanded jets from adjacent nozzles can cause flow reversal to-
wards the base of a launch vehicle. This can lead to high heat transfer to the base, which need to predicted accurately for the design of the base thermal protection system. It is pro-
posed to conduct CFD simulation of the multi-jet interaction problem, including the effects of non-equilibrium thermochemistry and turbulent heat transfer. Of particular interest is the nozzle wall ablation, which can alter the chemical composition and enthalpy of the re-versed flow, in turn affecting the base heat transfer rate. A three-dimensional Navier Stokes code will be developed for simulating the hypersonic turbulent reacting flows encountered in multi-jet interaction. The code will be validated and demonstrated for practical configurations of interest to VSSC/ISRO.
- Total Project outlay: Rs. 50.16 lakhs
- Duration and year of initiation: Three years, 2018