Karan Mudaliar

Pursuing, Master's in Aerospace Dynamics with experience in research and academic projects. Passionate about Aerodynamics and Fluid Dynamics. Resourceful, versatile and self-starter in all projects/research work. Competent leader with strong analytical skills and able to achieve objectives under strict deadlines. Having working knowledge of Gas Dynamics, Fluid Dynamics, Computational Fluid Dynamics, Flight physics and Composite Material. Experience in material fabrication, material testing, CFD Simulations, Wind-tunnel testing, and project management. Hoping to build a successful career in a diverse, innovative company and work on projects in various area of expertise.

• Co-authored a peer-reviewed research paper and published it in science direct (Elsevier). One of the leading studies to characterize the decay of Mechanical strength C-Ph composites treated with Aviation fuel. It was presented in an international conference for structural Integrity held in Italy, conducted online with 300 in attendance
• Studied the flow characteristics of Hypersonic re-entry Vehicles with Ansys Fluent and determined the best configuration for heat and drag reduction. Presented in a National conference with 300 in attendance
• Designed a conceptual Hybrid-electric turbojet engine and calculated its performance. Presented a paper in a national conference with 400 in attendance
• One of the Top ten models (Subsonic wind tunnel) in Aero-expo 2018 at Hindustan Institute of Technology and Science

MSc Aerospace Dynamics: Cranfield University,  Cranfield, UK (October 2021 - October 2022)

• Relevant Modules: Compressible Flows, Computational fluid Dynamics, Flight Dynamics Principles, Launch and Re-entry Aerodynamics, Fundamentals of Rotorcraft Performance, Stability and Control, Viscous Flow and Environmental Impact, Modelling of Dynamics systems, Transonic Aerodynamic Design, Experimental Aerodynamics, CFD for Aerospace.
• Group Project: "Flight Experimental Methods" (Group Flight Test Report). It involves up to seven separate flight tests in the National Flying Laboratory Centre (NFLC). The recorded Flight Data from JetstreamJ31 was analysed using MATLAB. The performance of the aircraft was assessed and validated for the manufacturer's data.
• Individual Research project: Unsteady Simulations of a Multi-Element High Lift NEXUS Wing Flow.  Computational investigations were carried out on three element High lift nexus wing, as part of the WINDY project. Unsteady simulations were carried out to capture the flow physics of the three-element wing in take-off configuration for A320 research wing. Ansys fluent was used to analyse the flow field and a shedding frequency of the flap was determined using the unsteady computational data.

B. Tech Aeronautical Engineering: Hindustan Institute of Technology and Science,  Chennai, India (June 2017 - June 2021)

• Relevant Modules: Fluid Mechanics, Thermodynamics, Solid Mechanics, Aerodynamics, Gas Dynamics, Aircraft Structures, Aircraft Propulsion, Computer Aided Design, Flight Dynamics, Experimental Stress Analysis, Composite Materials and Structures, Heat transfer, High Temperature Materials, Fundamentals of Computational Fluid Dynamics.
• Course group project: "Design of a Single Engine Utility Aircraft". The project started with specifications and parameters of thirty existing single turboprop utility aircraft. These were similar to aircraft under design. The compared and analysed parameters were the ideal design parameters. The airfoil, weight estimation, engine and other essential parameters/components of aircraft design were determined. The project concluded with detailed performance values and graphs.
• Final Year group project: "Drag and Heat Flux Reduction on Hypersonic Re-entry Vehicles in Combination with Different Aero-spikes". Computational investigations were carried out on blunt bodies with and without spikes, to know the flow behaviour at different High Mach Numbers. Effect on the coefficient of drag by changing the spike tips such as different Aero disks and spikes was studied. Furthermore, the effect of the heat flux on the spiked-body was also studied. Finally, conclusions were made on optimum aero-spike for heat flux and drag reduction.
• GPA: 8.99/10.00