Rupesh Kotapati, Ph.D. Email & Phone Number

Waltham, Ma

Upon acquisition of Exa Corporation.

Burlington, Ma

Burlington, Ma

Burlington, Ma

Burlington, Ma

Washington, Dc

– Aided the development of a Cartesian grid-based immersed-boundary, viscous, incompressible flow solver for simulating and optimizing flows over complex airfoil geometries using efficient multi-grid techniques. – Aided the development of a body non-conformal curvilinear mesh, sharp interface immersed-boundary, compressible flow solver based on the flux vector splitting scheme of Steger and Warming for solving flows over helicopter blades, submarine propellers, etc.– Carried out DNS of synthetic jets in quiescent air, and validated the simulation results using experimental measurements as part of a NASA Langley workshop on CFD validation of synthetic jets and turbulent separation control (Funded by NASA).– Designed and evaluated a novel flow configuration for investigating the active control of canonical separated airfoil flows.– Performed DNS and LES to study zero-net mass-flux (ZNMF) jet based active separation control of canonical separated airfoil flows using Stanford CTR’s unstructured grid CDP code (Funded by NASA and US AFOSR).

Stanford, Ca

– Investigated resonant interactions of characteristic system frequencies for multi-modal control of separated flows.– Used linear stability theory (LST) to evaluate the active control of laminar separation bubbles in numerical simulations.– Simulated the lift enhancement on a NACA 0015 airfoil by zero-net mass-flux (ZNMF) jets using Direct Numerical Simulations (DNS) and Large-Eddy Simulations (LES).

Tempe, Az

– Applied and validated Detached-Eddy Simulation (DES) and Spalart-Allmaras (S-A) turbulence model for predicting the high Reynolds number separated flow over static and maneuvering geometries of a prolate spheroid for the purpose of simulating the pitch-up maneuver of a submarine (Funded by US Navy – Office of Naval Research).– Developed and tested novel length scale definitions to address the existence of a “grey area” between the RANS and LES regions that leads to modeled-stress depletion (MSD) in the original DES formulation. – Applied and validated DES, S-A, and Shear-Stress Transport (SST) models to predict the high Reynolds number flow over Aerospatiale A-airfoil at maximum lift (Funded by US AFOSR as part of a Department of Defense Challenge Project).

Shar, Ap, India

– Applied and validated k-ε turbulence model to study the flow and thermal characteristics of a supersonic jet impinging on a jet deflector for the purpose of designing the second launch pedestal at Satish Dhawan Space Centre.

Executive Certificate, Management And Leadership

- Finance - Strategic Marketing - Developing and Managing a Successful Technology and Product Strategy - Managing Technical Professionals.

D.Sc./Ph.D., Mechanical & Aerospace Engineering

Major: CFD/Thermal and Fluid Sciences Minors: Computer Science, and Applied Mathematics Dissertation: On Synthetic Jets and Their.

Ms, Aerospace Engineering

Thesis: Detached-Eddy Simulation (DES) of Flow over a Prolate Spheroid Undergoing a Pitchup Maneuver (Funded by US Department of the Navy.

Be, Aeronautical Engineering

Thesis: Numerical Study (RANS) of the Flow Characteristics of a Supersonic Jet Impinging on an Axisymmetric Deflector (Funded by Indian.

Higher Secondary Certificate, Math & Physical Sciences