Justin Aholt
Missouri University of Science and Technology
Dept. of Mechanical & Aerospace Engineering
Advisor: Dr. Fathi Finaish, Advisor

Abstract
Wind Tunnel testing is of primary importance to the fields of engineering and physics. It has a wide range of applications, including, but not limited to, the testing of airfoils, wings, aircraft and ground vehicle models, research into the effects of wind on structure stability and sand movement, research on wind as a source of alternative energy, aircraft accident investigations, flow visualization and testing, endurance testing, boundary layer studies, and validation and development of theoretical and computer flow models. The Missouri University of Science and Technology has felt the need of a state-of-the-art wind tunnel facility capable of the activities listed above. It has conducted a feasibility study regarding the construction and operation of such a facility and has developed a conceptual design of the wind tunnel. This report briefly presents the design procedure used to develop the wind tunnel as well as the design of the tunnel itself. The designed tunnel is capable producing low-turbulent flow of velocities between 0 and 225 mi/h through a test section 32 in. tall and 48 in. wide. The tunnel designed is capable of producing flow velocities up to 225 mi/h. At this velocity, the tunnel would require a motor-fan arrangement capable of generating over 210,000 CFM and would correspond to dynamic pressures of about 6400 Pa and Reynolds numbers of more than 2.2 x 106 at 225 mi/h.