Dr. Balajee Ramakrishnananda got his Doctoral Degree from Nanyang Technological University, Singapore, in 1997. His doctoral thesis work centered around the computational study of flow through a centrifugal vaned diffuser used in transonic flow regimes.

He obtained his Masters degree from IISc, Bangalore and B. Tech. from IIT, Madras. Prior to joining Amrita, he was working as a Software Engineering Manager at AMD, Hyderabad in the area of GPGPU Computing.

Dr. Balajee had also worked as a Scientist-B at National Aerospace Laboratories, Bangalore in the area of Transonic Wind Tunnel Testing. He has worked for several years in the Military & Flight Simulation fields in product development and managerial roles. He had also worked on physics based animation where he placed aerodynamics and flight mechanics of birds in a perspective suited for computer animation. 


Publication Type: Journal Article
Year of Publication Publication Type Title
2013 Journal Article B. Ramakrishnananda, Krishnan, R., RevathyPriya, R. R., Basavara, A., and Santhanam, S. Ganapathy, “Aerofoils for Small Vertical Axis Wind Turbines”, National Conference on Wind Tunnel Testing (NCWT-03) [CD-ROM], 2013.
1999 Journal Article B. Ramakrishnananda and Wong, K. Cheong, “Animating bird flight using aerodynamics”, The Visual Computer, vol. 15, pp. 494-508, 1999.
Publication Type: Conference Paper
Year of Publication Publication Type Title
1994 Conference Paper B. Ramakrishnananda and M., D., “Numerical Study of Viscous Turbulent Flow Through Planar and Axisymmetric Nozzles”, in 14th International Conference on Numerical Methods in Fluid Dynamics, Bangalore, India, 1994.
1994 Conference Paper B. Ramakrishnananda and Damodaran, M., “Computational study of aerodynamic flows inside nozzles”, in International Pacific Air & Space Technology Conference, Singapore, 1994.[Abstract]

Compressible aerodynamic flows inside nozzles are computed by a finite volume method to numerically integrate the Euler and Navier-Stokes equations. The solution procedure is based on an explicit multi-stage time-stepping scheme wherein the spatial terms are central-differenced and a combination of second and fourth differences in the flow variables are used to construct numerical dissipation terms to enhance numerical stability. Convergence to steady state is accelerated dramatically by using local time-stepping, implicit residual smoothing and a multi-grid strategy. Computed results are presented for a wide variety of flow regimes comprising of subsonic, transonic, choked and supersonic flows for a nozzle. More »»
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