Ablative heat shields have been used to protect hypersonic vehicles during atmospheric reentry during the Apollo missions and could be used for future flight vehicles as well. Advances in computational models enable a large variety of vehicle shapes to be considered. However, it is exceptionally difficult to perform reliable tests at conditions which are representative of flight to validate the models. Historically, tests have been conducted on substitute materials at low temperatures to validate models, but even these tests can pose significant challenges. For example, most previous studies rely on model shape measured before and after tests or have relied on Schlieren photography for measuring changes in model profile only. Only recently has photogrammetry been used to quantify shape change in three dimensions for the ablative models. In our study, the AFIT Mach 3 pressurevacuum wind tunnel was used in combination with models consisting of dry ice to collect ablation data for models of different shapes at stagnation pressures ranging from approximately 0.4 atm to 3 atm and stagnation temperatures equivalent to room temperature. High speed Schlieren photography was used for visualization, and the three dimensional shape change was quantified with sub-millimeter accuracy using laser dot photogrammetry. Results for one shape are compared to those computed using a computational model, which employs a finite-volume approach to solving the (3-D) NavierStokes equations, with the gas assumed to be at equilibrium, while employing an implicit solver accounting for the material response. Increased stagnation pressure led to larger material loss in the stagnation region of the model, as expected.