Research & Development of Engineering. Instruments, Business Initiatives & Project Planning

Fabrication of 2-D Air-intake nozzles, single wedge and double wedge air intakes got fabricated for different supersonic Mach numbers (M=2.1, 2.5, 3.0) for experiment in the 1"x3" Supersonic Wind Tunnel at I.I.Sc., Bangalore and Flow visualisation and pressure measurements were performed. Further computational studies were performed for flow properties after compression, expansion and different combination of two with the help of program. Program to find area ratio and downstream pressure.A two fin LCA aircraft model (R80) for various force and moments were tested aerodynamically to check the characterstics in the Mach number range of 0.40 to 1.80 with pitching angle range from -5 to 20 degree.I have been engaged in the wind tunnel testing aerodynamically for Agni missile, upto Agni-2