Imagination is more important than knowledge. For knowledge is limited to all we now know and understand, while imagination embraces the entire world, and all there ever will be to know and understand.

                                                                                                                                            —Albert Einstein

Nishul Arora

Three Dimensional Shock Boundary Layer Interaction

His research is focused on gaining more insight into the dynamics of 3D SBLI. This study is a part of larger research including four universities - Florida State University, University of Texas at Austin, Ohio State University and University of Auburn. The primary goal of this research is to develop on the knowledge of the unsteady characteristics of SBLI and mitigate some of the adverse effects of it by carefully placed perturbations. Currently at FSU, the focus is on studying the interaction of a fin generated swept shock with the incoming boundary layer. In practical world, this type of configuration is commonly encountered at the fin/tail fuselage junction (external flow) and inside the inlet of a supersonic aircraft (internal flow). Various techniques such as two and three component PIV, steady and unsteady pressure measurements and high speed conical shadowgraphy has been utilized to study this problem.

  •   Arora, N., Ali, M. Y., Zhang, Y. and Alvi, F., "Shock Boundary Layer Interaction due to a Sharp Unswept Fin in a Mach 2 Flow" 53rd AIAA Aerospace Sciences Meeting.

  •   Zhang, Y., Sun, Y., Arora, N., Cattafesta, L., Taira, K., & Ukeiley, L. (2015). Suppression of Cavity Oscillations via Three-Dimensional Steady Blowing. In 45th AIAA Fluid Dynamics Conference (p. 3219).​

  •   Topolski, M., Arora, N., Ali, M., Solomon, J., & Alvi, F. (2012, June). Experiments on resonance enhanced pulsed microjet actuators in supersonic cross flow. In 6th AIAA Flow Control Conference. doi (Vol. 10, No. 2514, p. 6).