Wind Tunnel - Launch Vehicle Aerodynamic Testing

Project number: 
Northrop Grumman
Academic year: 
Design a wind tunnel to evaluate airflow over different airfoil and nose cone designs. The wind tunnel will be designed to visually display and record the airflow, this data will be used determine the efficiency of different geometries and drive design improvements. The wind tunnel will allow for various speed inputs to evaluate the test object at different stages of flight. In addition, the test chamber will include mounting support to adjust the angle of the test object.

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