Solid rocket motor (SRM) exhaust contains chlorine, an important stratospheric constituent that plays a crucial role in the chemistry of ozone. Models of SRM plume combustion and chemistry suggest that a significant fraction of SRM exhaust chlorine might be in an active form as a result of afterburning reactions and be available for immediate ozone destruction as the plume mixes with the ambient stratosphere. If afterburning does produce free chlorine, the SRMs used by the Titan IV and Space Shuttle have the potential to cause nearly complete ozone loss in regions up to several tens of kilometers in radius, depending on altitude. We present a simulation of SRM exhaust mixing and chemistry that predicts the three-dimensional structure of the prompt local ozone loss during the 8 h following a daytime Titan IV launch. Maps of the loss of the total column ozone abundance show that the maximum loss of about 30% occurs about one hour after launch, Four hours after launch the area of column ozone loss exceeding 8% covers up to 2000 km(2). The shape and severity of the ozone-depleted region depends only slightly on the interaction between launch trajectory and stratospheric winds. Solar ultraviolet flux on the ground beneath the plume changes in response to decreased ozone absorption, alumina scattering, and absorption by chlorine oxide compounds. The ultraviolet flux increases by 100% at 295 nm, shows no change near 300 nm, and decreases by 30% longward of 310 nm. Existing space instrumentation does not possess the spatial resolution required to measure ozone depletion of the size and magnitude predicted following launches involving large SRMs.