Profile

Dr.Debasis Chakraborty did his Ph.D in Aerospace Engineering from Indian Institute of Science (IISc), Bangalore. He has worked in VSSC and DRDL for the last 32 years and currently he is working as technology director of Directorate of Computational Dynamics (DOCD) in DRDL. He has worked extensively in numerical simulations of high speed reacting and non reacting flows and provided useful aerodynamics and propulsion design inputs for satellite launch vehicle, strategic and tactical missiles. He is the fellow of Indian National Academy of Engineering, Institute of Engineers and Aeronautical Society of India and has received many awards including DRDO Scientist of the year, DRDO award for best innovation/futuristic development etc. He was the INAE-AICTE Distinguished Visiting Professor at IISc, Bangalore, and visiting professor at University of Hyderabad. He has published more than 235 research papers in various international journals and conferences in the area of CFD. As guest editor, He editeda special issue of Defence Science Journal on CFD.He was a member of aerodynamics and propulsion panels of AR&DB and expert panel member of National Supercomputing Mission and National Center for Combustion Research and Development (NCCRD).

Title of the Talk

High speed air-breathing missile propulsion design through CFD simulation

Abstract

Application of reacting CFD tools in the design and analysis of high speed airbreathing systems are described. The computational tool has been validated extensively against reliable experimental data before applying it into design exercise. Different fuel injection schemes and strut arrangements are considered to obtain an optimized performance of a flight sized hydrocarbon fuelled scramjet combustor. Very good match of the top wall pressure has been obtained with experimental data for both nonreacting and reacting flows. Computed convective heat flux obtained through well resolved thermal boundary layer simulations is used in the thermo-structural analysis of the scramjet combustor. End-to-end simulations integrating both external (nonreacting) and internal (reacting) flow are carried out of a complete hypersonic/supersonic air-breathing vehicle to obtain complete aerodynamics and propulsion parameters of the vehicle for mission design. The evaluated installed air intake performance in terms of pressure recovery and mass capture ratio match very well with experimental data. Significant variation of intake performance is observed between windward and leeward intakes for higher angle of attack and the leeward intake move towards the subcritical operation faster. The intake flowfield is seen to interact with the corebody boundary layer causing significant spillage. The starting and unstarting characteristics of a hypersonic intake is evaluated through unsteady RANS simulations. Both started and unstarted flow with large pressure oscillation is captured for different Mach numbers. The use of CFD tools has reduced the dependence of experimental testing in the design of high speed airbreathing propulsion systems.