Research

Hypersonic Shock Tube Facility — Design & Fabrication

Postdoctoral Research 

2023-Present

Florida Center for Advanced Aero-Propulsion (FCAAP), Florida A&M University-Florida State University College of Engineering, USA.

PI: Prof. Rajan Kumar

The hypersonic shock tube is designed for advanced shock impact studies and high-speed flow visualization. The facility features a 4.5 × 4.5-inch square test section with clear side windows, enabling techniques like schlieren imaging and particle image velocimetry (PIV) to capture detailed flow behavior in real time. To be built at the FSU Engineering Machine Shop, the facility is precision-fabricated for safety, repeatability, and high-pressure operation. Its modular design allows for easy configuration changes, while the round-to-square transition and high-quality optical windows ensure accurate, distortion-free measurements. This cutting-edge setup supports experiments in shock physics, aerodynamics, and hypersonic flow research, including material testing studies combining robust engineering with advanced diagnostics to push the boundaries of high-speed fluid dynamics.

Supersonic Flow Visualization over a Floor-Mounted Hemisphere

Postdoctoral Research 

2023-Present

Florida Center for Advanced Aero-Propulsion (FCAAP), Florida A&M University-Florida State University College of Engineering, USA.

PI: Prof. Rajan Kumar

We conducted Particle Image Velocimetry (PIV) and schlieren visualization experiments on a floor-mounted hemisphere at Mach 2.0. These studies produced high-quality data, and advanced analysis techniques such as Proper Orthogonal Decomposition (POD) and Dynamic Mode Decomposition (DMD) were used to reveal detailed flow structures and dynamics.

Impinging Jet Interaction with Flexible Ground Structures

Postdoctoral Research 

2023-Present

Florida Center for Advanced Aero-Propulsion (FCAAP), Florida A&M University-Florida State University College of Engineering, USA.

PI: Prof. Rajan Kumar

Impinging jets, like those from STOVL aircraft hovering over a deck, can generate strong, steady, and unsteady loads, sometimes causing resonant pressure oscillations that threaten structural integrity. In this study, a Mach 1.5 jet at various expansion conditions impinges on ground planes with different levels of compliance. Using digital image correlation, high-speed shadowgraphy, and acoustic measurements, we investigate how flexible panels respond to flow oscillations, how the flowfield evolves, and whether noise is amplified or reduced. This work explores bidirectional flow-structure interactions and aims to inform safer, quieter designs for structures under jet impingement.

Shock Focusing Facility

2018 – 2023 (During Doctoral studies)

Hypersonic Experimental Aerodynamics Laboratory (HEAL), Indian Institute of Technology Kanpur, India 

A contoured converging section was designed, fabricated, and integrated into an existing shock tube to generate spherically focused shock waves. The facility is equipped for spectroscopic, thermocouple, and unsteady pressure measurements, enabling detailed characterization of the focused shock field. Complementary numerical simulations (ANSYS Fluent) provided further insight into the flow features and validated experimental observations.

Supersonic Cavity Flows

2015 - 2017 (During Master’s studies)

Birla Institute of Technology, Mesra, India

A rectangular cavity (L/D = 3.6) was investigated at Mach 2.0 using both experiments and numerical simulations. Various impinging wall and floor modifications were tested to reduce pressure fluctuations. Results showed a clear reduction in tonal peaks and overall sound pressure levels with passive wall modifications. Numerical simulations using ANSYS Fluent matched closely with experimental findings, validating the effectiveness of the control strategies.