Structural damage from sonic booms is one of the potential environmental impacts of supersonic flight. This paper illustrates how structural acoustic techniques may be used to assess the potential for such damage in the absence of actual flyovers. Procedures are described whereby transfer functions relating structural response to sonic boom signature may be obtained with a stationary acoustic source and appropriate data processing. Further, by invoking structural acoustic reciprocity, these transfer functions may also be acquired by measuring the radiated sound from a structure that is mechanically driven. The approach is based on the fundamental assumption of linearity, both with regard to the (acoustic) propagation of the boom in the vicinity of the structure and to the structure’s response. Practical issues revolve around acoustic far field, source strength, and directivity requirements. The technique was evaluated on a specially fabricated test structure at Edwards AFB, CA. Blank shots from a cannon served as the acoustic source and taps from an instrumented hammer generated the mechanical drive. Simulated response functions were constructed. Results of comparisons with corresponding measurements recorded during dedicated supersonic flyovers with F-15 aircraft are presented for a number of sensor placements. Using the prediction of peak structural response as a metric, it was found that the direct and reciprocal simulation techniques produced ensemble-averaged mean percent errors of −4% and −26%, respectively. The corresponding standard deviations of these errors were 18% and 16%. Also, it was concluded that these uncertainties are consistent with that connected to the representation of the sonic boom itself.