Adjoint Optimization of the Spatial Profile of Steady Energy Deposition for Supersonic Drag Reduction
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2015, American Institute of Aeronautics and Astronautics, Inc. The interaction between localized volumetric heating and planar geo-metric bodies in steady, supersonic flight is examined with emphasis on quantifying the drag reduction achievable by tailoring the spatial distribution of the heat source. The adjoint optimization technique is used to characterize the baseline (zero energy addition) drag reduction slope efficiency as a function of body shape and Mach number. The results show close agreement with an isobaric heating model. At non-zero heat deposition, the adjoint solutions are used to tailor the heating profile to achieve maximum drag reduction for cylinder, wedge and power-law bodies. Several methods of modifying the heat release profile are presented and compared. The resulting energy optimization shows distinct differences in slope efficiency between sharp edged and blunt bodies, although in both cases drag reduction is maximized with long, thin profiles of heat deposition.