Aerodynamic design, analysis, fabrication and testing of a claw yaw sphere for subsonic flow

Abstract

Modern day aerodynamics has applications in various domains ranging from design of ballistic shells to ground vehicles exceeding sonic speeds. The conceptual design and analysis of such extreme applications require test beds of the same calibre which are able to comply with the complexity of the working mechanism. Wind tunnel is one such apparatus where scale models of the prototypes can be tested. Alike all apparatus even wind tunnels has to be calibrated on a regular basis which ensures that the readings obtained from the instrument are acceptable and the error margin are within the limitations. Thus there is a need for instruments which can accurately measure the various properties of the wind tunnel, namely the flow angularity, velocity distribution, speed setting etc. Taking into account the various requirements a claw yaw is designed, simulated and tested in a wind tunnel and the results are discussed.