This experimental project aims to analyze the supersonic flow over blunt nose cone models in a supersonic wind tunnel. The project involves designing and fabricating nose cone models with different dimensions named as BNC-I, BNC-II and BNC-III. The models are tested in the Supersonic wind tunnel facility and Schlieren flow visualization setup which is located at HITS, Chennai to measure their aerodynamic characteristics and shock wave phenomenon. The Nose cone model is fixed in the test section of the supersonic wind tunnel and mach number is manipulated by varying settling chamber pressure to reach the supersonic mach number of 1.7, 2 and 2.5 and to capture the shock formations. High resolution camera is used for capturing the flow patterns and pressure distributions around the nose cone models. The data collected is analyzed and compared to identify the differences in aerodynamic performance between the different dimensions of the blunt nose cone models. The results of this study will provide valuable insights into the design and optimization of nose cone models for supersonic applications, such as aerospace vehicles and missiles designs.