The intense noise radiated by supersonic hot jets leads to sound-induced structural vibration, fatigue and personnel-related operational difficulties. Experimental, theoretical, and computational investigations into the physics and control of jet noise have identified several important sound sources, including wavepackets, screech, Mach wave radiation, and broadband shock associated noise. Reducing the loudest sources of jet noise, without sacrificing propulsive performance, has relied on intuition, parametric survey, or optimal control techniques. With the aim of developing a more general and robust method of jet noise reduction, we present a physics-based approach, built upon a linear resolvent analysis, and apply it to reduce the noise generated by a biconical tactical jet nozzle. Our approach identifies optimal forcing/response modes of the compressible Navier-Stokes operator, linearized about a jet mean flow, that best disrupt the coherent structures that are primarily responsible for the production of jet noise. The operating conditions of the jet and nozzle geometry are motivated by tactical Naval aircraft.