HYPERSONICS

Research Activities

NUMERICAL MODELLING OF HyShot II

Iso-surface of pressure at 180 kPa, coloured by the Mach number;

H2O distribution: on bottom slice

Transversal, 90° H2 injection into the incoming airstream generates very complex flow structures.


Vorticity generated in this way may be understood better by looking at the Crocco-Vazsonyi equation:

Isosurface of H2 at 0.01 mass fraction;  color maps OH

Isosurface of H2 at 0.01 mass fraction colored by H2O

Temperature distribution at X=0.028 m ; H2 distribution on  bottom slice

Isosurface of H2 at 0.01 mass fraction; color maps Temperature


NUMERICAL MODELLING OF HIFiRE 2


NUMERICAL MODELLING OF EXPERIMENTAL TEST CASE

RAMJET RESEARCH

Scale demonstrator of liquid air-kerosene and/or solid Ramjet engine capable of carrying out tests to verify functionality and calibration of cold and hot mathematical models

COMPUTATIONA FACILITY

We have a sophisticated high tech workstation with the following configuration to support our research activities.

A computer equipped with 

   (48 Processors)

Other Computers to meet the day to day academic needs

FUTURE PLANS OF INSTALLING TEST FACILITY

The establishment of a test facility that could meet the current research activities in Hypersonics and thereby conducting cutting-edge research in anticipation of future propulsion solutions 

PHASE 1 :


Blowdown-type hypersonic wind tunnel for flight tests at Mach 2-5 in the order of 10-30 s (depending on the flight Mach and thrust target)