Advanced diverterless supersonic inlet (DSI) geometries were numerically investigated in a wing-fuselage installation. Generic models were created and used in order to study the basic aerodynamic behavior of such DSI configurations. Optimization processes led to the improvement of the bump-to-inlet area ratio, which has been determined as one major design driver. The computational results of the generic investigations served as a basis for a more configurational application of a DSI.
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