A family of five axisymmetric external compression inlets was tested at Mach 1.97 in the 1-ft × 1-ft supersonic wind tunnel at the NASA Glenn Research Center. AU five inlets shared the same external compression surface; they differed only in subsonic diffuser geometry. The external compression surface used an isentropic relaxed compression design developed by Gulfstream Aerospace Corporation. Steady-state pressure data were recorded on the inlet centerbody, on the cowl, and at two pitot pressure rakes located at the aerodynamic interface plane (AIP). High frequency dynamic pressure data were recorded at one static pressure tap on the inlet centerbody and at a pitot probe on the AIP. Schlieren images were also recorded. This paper analyzes the dynamic pressure data from three of the inlet models.