In this work, the experimental approach was used to study the aerodynamic performance of cylindrical mid-section with various forebody profiles. The aerodynamic characteristics, such as static pressure, axial velocity, and coefficient of pressure for cylindrical mid-section with various forebody profiles were investigated for subsonic speed for the same length-to-diameter ratio. The experimental work was conducted at a flow velocity of approximately 25 m/s and calculations were done for zero degrees angle of attack to demonstrate the flow behavior. The experimental data of each test was compared to find out the deviation between static pressure, and axial velocity. From the study, it is concluded that the sharp tip forebody profiles have a small stagnation region over the cylindrical mid-section and the blunted tip of the forebody has a bigger stagnation region over the cylindrical mid-section, therefore the aerodynamic properties vary over the cylindrical mid-section-due to the shape of various forebody profiles. Thus, the cylindrical mid-section with power series 1.0 forebody reaches greater velocities with low static pressure from leading to the trailing edge.

orebody, aerodynamic performance, cylinder, wind tunnel

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