An experimental investigation of the time varying distortion at the diffuser exit of a subscale HiMAT fore body and inlet was conducted at Mach 0.9 in the Lewis 8 by 6 Foot Supersonic Wind Tunnel. A transitory separation was detected within the subsonic diffuser . Vortex generators were installed to eliminate the flow separation . This paper will present results from a study of the instantaneous pressure variations at the diffuser exit . The time unsteady total pressures at the diffuser exit are computer interpolated and presented in the form of a movie showing the transitory separation. Limited data showing the instantaneous distortion levels is also presented.Nomenclature

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