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10/25/2009
On October 25, 2009, Advanced Dynamics Corporation released the Word's first multi-disciplinary, multi-physics, multi-scale and multi-fidelity analysis amd design optimization (4MAO) ......
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For immediate inquiries call Tel: (859) 699-0441 Fax:(859) 243-5615 Email: Contact@advanceddynamics-usa.com


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Nagendra Dittakavi, PhD
Research Scientist

Tel: 859-699-0441
Fax: 859-243-5615
Nagendra.Dittakavi@AdvancedDynamics-USA.Com


Dr. Dittakavi obtained his Master’s and PhD degrees from School of Mechanical Engineering, Purdue University. His research interests include Computational Fluid Dynamics (CFD), Combustion, Multiphase Flows, and Acoustics. During his graduate studies he developed Direct Numerical Simulation (DNS) and Large Eddy Simulation (LES) techniques to study flow generated sound from free and confined flows. He also worked as a summer intern in the Rolls-Royce combustion group to develop their LES code. He joined Advanced Dynamics Inc. (ADI) in February 2009 as a research scientist. At ADI his research includes modeling and simulation of flows involving turbulence, combustion, high speed flows, jet noise prediction using high-fidelity numerics and state-of-the-art modeling techniques. He is also involved in the development of the CFD Propulsion and Computational Aeroacoustics modules of the ASTE-P software.

Sample Results for Computational Aeroacoustics Using Large Eddy Simulations


Near-field vorticity magnitude
and far-field sound (shown using dilatation contours) for free jet using our LES code.

Isosurface of vorticity magnitude
colored with axial velocity
for subsonic free jet using LES.
Sample Results for Turbulent Combustion Using Large Eddy Simulations

(a) Temperature

(b) Reaction rate
Instantaneous snapshot showing contours of (a) Temperature, (b) Reaction rate for premixed reacting flow in a sudden expansion combustor.

Predictions of mean of temperature for reacting flow using LES (solid lines) compared with experimental measurements (symbols) premixed reacting flow in a sudden expansion combustor.
Sample Results for Supersonic Jet Impinging on a Wall Using Large Eddy Simulations

Instantaneous snapshot of density contours for supersonic jet impinging on a wall. Waves propagating between the impinging wall and the upper lift wall can be seen in the density contours.
Headquarters: Advanced Dynamics Inc. 1500 Bull Lea Road, Suite 203, Lexington, KY 40511
For immediate inquiries call Tel: (859) 699-0441 Fax:(859) 243-5615 Email: Contact@advanceddynamics-usa.com

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