AERO-PROPULSIVE DESIGN OF MISSILES THROUGH CFD
Dr. Debasis Chakraborty
Outstanding Scientist, Associate Director (Technology)
Defence Research and Development Laboratory (DRDL), Hyderabad
21 August 2019, 4.00-5.00PM
Auditorium, Department of Aerospace Engineering, IISc-Bangalore
Abstract
Over the last few decades, CFD has developed into a rich and diverse subject, and has emerged as a major component of applied and basic fluid dynamic research along with theoretical and experimental studies. CFD methods are employed routinely for the estimation of various complex aerodynamic and propulsion flow parameters where obtaining experimental data is not economically or technically feasible. In DRDL, missile designers depend heavily on CFD techniques for the accurate prediction of various aerodynamic and propulsion parameters in the design exercise and thus contributing significantly in reducing developmental cost and time.
DRDL has developed a host of indigenous grid generators and flow solvers using advanced numerical techniques and physical models. After systematic validations against reliable experimental results, these codes are routinely used to estimate various aerodynamic parameters of DRDO missile systems. Aerodynamic characterization of various missiles in complete M- flight regime, control surface deflection studies, heat shield separation, store separation from aircraft, etc., are some of the notable applications of these codes. New indigenous software for Large Eddy Simulation (LES) is developed and validated for many stringent canonical problems and are currently being applied to different engineering problems involving separated flows.Core competencies are developed in numerical simulation of turbulent reacting flows. Commercial codes were validated extensively to find its error band and application range. Design of hydrocarbon-fueled scramjet combustor, estimation of integrated aero-propulsive data for mission design of hypersonic airbreathing vehicle, jet vane design for various tactical missiles, air intake characteristics estimation, exhaust plume–free stream interaction etc. are some of the notable examples. Key performance parameters were predicted, and propulsion systems were optimized through the analysis of various computed thermochemical parameters.
An overview of the development and application of CFD techniques for aero-propulsive characterization of various DRDO missile systems will be presented.
Dr. Debasis Chakrabortyis an Outstanding Scientist in DRDO and works as theAssociate Director (Technology) and Group Director (Design) in Defence Research and Development Laboratory (DRDL), Hyderabad.He received his M. Tech from IIT, Kharagpur and Ph.D. in Aerospace Engineering from IISc. Bangalore. He has worked as a Scientist/Engineer in Vikram Sarabhai Space Center (VSSC), ISRO, Thiruvananthapuram from 1986 to 2001 and wasinvolved in Aerodynamic design and analysis of various sounding rockets and satellite launch vehicles of ISRO.In DRDL,he and his group has developed indigenous CFD codes for aerodynamic characterization of different tactical and strategic missiles, store separation design of missiles from fighter aircraft etc. He is also the leader of DRDO-DDR&D (Indo-Israel) CFD working group. Currently, As Group director of the design group, he is currently supervising various activities of mission, aerodynamic, Flight structure, thermal and computational issues of missile design are being pursued. Additionally, activities of Hypersonic Technology Demonstrator vehicle (HSTDV) and Hypersonic Wind Tunnel (HWT) projects are also being supervised by him. He is a Fellow of Indian National Academy of Engineering, Aeronautical Society of Indiaand Institute of Engineers (India). He has received DRDO scientist of the year award in 2012 and several other awards.
Date/Time
Date(s) - 21/08/2019
4:00 pm
Aerospace
Categories