HYPERSONICS

Research Activities

Scramjet Supersonic Combustion Modeling – studying high-speed combustion processes
Fuels and Injection Techniques – with emphasis on DMR engines
High-Performance Scramjet Optimization – design and performance enhancement
Computational Fluid Dynamics (CFD) – simulations and algorithm development
Ground and Flight Testing – under realistic flight conditions
Design Optimization – maximizing efficiency, performance, and safety

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

The research focuses on the understanding of the start-unstart nature of the scramjet by simulating cold flow, cold flow with injection and hot flow.
The Numerical simulations were carried out using RANS AND LES codes within the commercially avaible codes to Investigate the effect of different geometries, length, fuel injection angles that could help in understanding how to improve the design of scramjet engines.
The research aims to improve the combustion efficiency by decrease pressure losses.
Understanding of the combustion mechanism and improving chemistry of combustion by implementing new reaction mechanisms.
Aims to better understand the flow behaviour and vorticity nature.

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

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)

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