Shock/boundary-layer interaction and attendant flow separation is a common and detrimental phenomenon occurring in high-speed flight, which can happen on aircraft wings, missile fins, and supersonic intakes. The occurrence of flow separation can lead to unsteady loads on wings and buffeting, unpredictable force generation on control surfaces, and boundary-layer distortion leading to total pressure loss and intake unstart. It is imperative to mitigate flow separation, using active (requiring actuation) or passive (not requiring actuation) mechanisms. Examples of active flow control methods include boundary-layer suction and blowing, heating/cooling of walls etc. and examples of passive flow-control devices include vortex generators and porous surfaces, all of which modify the flow close to the surface and make the flow more resistant to separation. The webinar addresses shock/boundary-layer interaction in canonical and realistic configurations and flow control using active/passive techniques.